SDI Guided Munitions Catalog [DO NOT POST]

by **The Technocratic Syndicalists** » Wed Jul 13, 2016 11:04 pm

RBS 88 Waverider

General Characteristics:
Type:
Hypersonic Cruise Missile

Launch platform:
Aircraft

Guidance:
Stellar-inertial, GPS
Physical Characteristics:
Weight:
1,000 kg cruiser, 2,300 kg with booster

Length:
4.0 m cruiser, 6.3 m with booster

Diameter:
0.6 m

Payload:
RBS 88A:
4x Rb 71 loitering munitions

RBS 88B:
2x PC 100S hart target submunitions
Performance Characteristics:
Propulsion:
Dual mode scramjet (sustainer), solid fuel rocket (booster)

Speed:
Mach 8.0

Cruise altitude:
30,000 m

Range:
2,500 km

Overview:
The RBS 88A Waverider cruise missile is a long range, air launched hypersonic cruise missile intended to penetrate heavily defended airspace and destroy hardened and time-critical high value targets deep inside protected enemy airpsace.

Airframe & Propulsion:
The Waverider is a two-stage missile and consists of a scramjet powered cruiser stage attached to a solid-fuel rocket booster. After being released from the aircraft the booster is ignitor and accelerates the missile to a speed of mach 4.5 at an altitude of 25,000 meters at which point the scramjet engine is lit and the solid fuel booster discarded. The cruiser stage has a rectangular, lifting-body geometry and consists of a wedge nose inlet, an under slung scramjet engine, and four rear mounted control fins. The cruiser is constructed primarily from Ti-6242S (Ti-6Al-2Sn-4Zr-2Mo-0.1Si) near-alpha titanium alloy covered with a silica-based ceramic matrix composite (CMC) thermal protection system designed to endure the >1,000° C skin temperatures of mach 8 cruise. The wedge shaped nose of the cruiser, which has to endure a leading edge temperature of over 1,600° C during mach 8 cruise, is constructed from carbon/carbon (C/C) ceramic matrix composite with a HfB2‐SiC (silicon carbide fiber reinforced halfnium diboride) ultra high temperature ceramic (UHTC) coating. The four control fins of the cruiser are constructed from cast titanium-aluminide (TiAL) intermetallic alloy with UHTC coated carbon/carbon (C/C) leading edges and are actuated using a 55 MPa hydraulic system driven by power takeoff from the engine fuel turbo-pump. The cruiser stage is attached to a solid-fuel booster which consists of a graphite-epoxy wound solid fuel rocket motor with a thrust-vectoring nozzle and four rear mounted control fins which provide aerodynamic control during booster operation.

The cruiser stage of the Waverider is powered by an SDI SRM 200 scramjet engine, a rectangular dual-mode scramjet (DMSJ) engine integrated into the underside the missile. The scramjet is fed using a fixed geometry 2-dimensional mixed compression nose inlet which consists of an aerodynamic compression ramp, sidewalls, a cowl lip, and an inlet duct which leads into the scramjet throat. The inlet ramp and walls of the scramjet engine are constructed from C/SiC (Carbon fiber-reinforced silicon carbide) ceramic matrix composite with service temperature of 1,900° C and are actively cooled by pumping endothermic hydrocarbon fuel through heat exchangers located alongside the walls of the scramjet engine where endothermic cracking of the hydrocarbon fuel is used to reduce the extremely high heat load experienced by the scramjet engine structure at hypersonic speeds. The dual mode scramjet engine that powers the waverider is capable of operating as either a ramjet or scramjet, known as "dual-mode" operation. The dual-mode scramjet consists of four sections, an inlet, a constant volume isolator, a combustor, and a nozzle. The dual-mode scramjet is lit at mach 4.5 and initially operates as a ramjet, decelerating the flow to subsonic speeds before combustion, with combustion taking place at constant pressure. As the mach number is increased past 5 the the subsonic ramjet transitions into the dual-mode regime, where the combustor inlet Mach number is increased enough such that a thermal throat is created in the combustor and a pre-combustion shock train is generated. The isolator is designed to prevent this shock train from reaching the inlet to prevent inlet unstart which would choke the engine of airflow. In this regime the combustor operates in a mixed subsonic/supersonic, or dual-mode. As the Mach number is further increased past 6 the pre-combustion shock train moves out of the isolator and the combustor operates in the supersonic mode with combustion taking place at a constant volume, rather than at a constant pressure like in the subsonic combustion regime. Endothermic hydrocarbon based fuel is injected into the combustion chamber via a series of regeneratively cooled ramp injectors constricted from sintered silicon nitride (Si3N4) which are recessed into the walls of the scramjet. The ramp injectors are designed to provide the minimum possible flow losses and maximize fuel mixing with supersonic airflow to maximize combustion efficiency.

The scramjet engine is fueled with methylcyclohexane (MCH), an endothermic hydrocarbon fuel which undergoes thermal cracking at high temperatures in the presence of a catalyst, undergoing catalytic dehydrogenation and yielding hydrogen gas and new hydrocarbon compounds while absorbing a significant amount of heat without forming any surface deposits. The MCH fuel is housed in a nitrogen inerted graphite/polyimide composite alloy tank in the center of the cruiser where it is pressurized to 100 bar using a turbopump and then pumped through a set of catalyst lined heat exchangers constructed from beta 21S (15Mo2.7Nb3Al0.2Si) beta titanium alloy located inside the C/SiC walls of the engine. The B21S titanium alloy is insulated from the C/SiC walls with a small air gap, ensuring the beta 21S titanium stays within its 675° C operating temperature. Inside the heat exchangers the catalyst and the radiant heat from the C/SiC scramjet walls causes the methylcyclohexane to decompose into hydrogen, cyclohexene, and various alkylcyclohexenes. The gaseous hydrogen, cyclohexene, and alkylcyclohexenes are then expanded through a gas turbine driving the fuel turbopump before being injected through the recessed ramp injectors into the combustion chamber where the fuel ignites with the combustion chamber air and is then expanded through a high-expansion ratio SERN (single expansion ramp nozzle) to generate thrust.

Guidance:
The Waverider is guided in flight by a stellar-inertial guidance system which provides highly accurate midcourse guidance without reliance on GPS signals. The guidance system consists of a 6-axis SDI TNS 450 tactical-grade timing and inertial measurement Unit (TIMU) which combines three milli-Hemispherical Resonator Gyroscope (mHRG) and three quartz resonating beam accelerometers (RBA) in a low SWaP package (500 cc volume, <1.0 kg mass, <5 watts max power consumption) package which provides <0.0003°/√hr gyro angle random walk and < 0.0001 °/hr bias stability performance coupled to a CCD star-tracker camera which looks upward through a circular window located in the upper fuselage of the cruiser stage. The star tracker employs is uses to provide position fixes in flight accurate to within 90 meters in broad daylight using a pre-programmed 57 star catalog. The IMU and stellar sensor are further augmented by a 48 channel dual-frequency (L1/L2) SAASM (Selective Availability Anti-spoofing Module) based GPS receiver with M-Code compatibility and >90 dB J/S digital anti-jamming capability whuch employs twin controlled reception pattern antennas (CRPAs) on the aft fuselage of the cruiser with adaptive beam steering and directional nulling capability with ionosphere correction capability and simultaneous L1/L2 operation which provides the weapon with <1 meter position accuracy capability. in heavy GPS jamming environments.

Warhead:
RBS 88A: The RBS 88A is designed to attack time-critical relocatable targets including mobile surface-to-surface and surface-to-air missile batteries and dispenses a payload of four Rb 71 loitering autonomous submunitions onto the target area. Each Rb 71 submunition weighs 38 kilograms and consists a maneuvering airframe 90 centimeters long with a 1.2 meter wingspan powered by a small turbojet engine which contains a solid state LADAR sensor with automatic target recognition (ATR) capability coupled with a multimode explosively formed penetrator warhead. The Rb 71 is powered by a 130 N thrust SDI RM55 micro-turbojet engine which gives the munition a maximum speed of 430 kph (Mach 0.30) an an altitude of 250 meters AGL with a maximum range of 185 kilometers and a maximum flight endurance of 30 minutes. The munition's seeker consists of a solid state three-dimensional imaging LADAR sensor employing an uncooled, diode pumped Nd:YVO4 laser with a 1.06 μm wavelength. The LADAR seeker is capable of acquiring vehicle size targets at a range of 6 km in clear weather and produces high resolution 3D imagery which is processed by an automatic target recognition processor which compares the LADAR image to a database of threat vehicles.

When the munition identifies a target it cuts its turbojet engine and glides towards the target to a point directly overhead where the munition's downward firing explosively formed penetrator (EFP) warhead is then fuzed. The warhead weighs 8.0 kilograms including 2.5 kg of polymer bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB) and can be miniated in one of three modes depending on target type and standoff range. Against armored targets the warhead is fired in a long rod penetrator mode which is designed for maximal armor penetration. Alternatively if fuzed from a greater altitude over the target the warhead is fired as an aerostable slug which maintains aerostability over greater standoff ranges while still having the capability to penetrate the thinner roof armor of most vehicles. Against softer targets such as TELs or radars the warhead is used in a directed fragmentation mode which causes the tantalum liner to break up into shrapnel which is projected towards the target area like a large shotgun blast.

RBS 88B: The RBS 88B is designed to penetrate and destroy hardened aircraft shelters, command bunkers, and other hard targets and contains a payload of twin PC 100S bombs which are released from the cruiser stage at high supersonic velocity prior to impact. Each PC 100S weighs 110 kilograms and employs a 100 kilogram hardened penetrator warhead consisting of a nickel-molybdenum-cobalt maraging steel (8Ni-14Mo-20Co-Fe) sub-caliber penetrating warhead filled with 20 kilograms of enhanced blast thermobaric explosive (50% HMX, 30% Al powder, 20% PCP/TMETN energetic binder/plasticizer). The warhead is fitted with a base mounted hard target smart fuze (HTSF) containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The detonator is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge. The warhead is coupled to a guidance and control section consisting of a 6-axis SDI 500 MEMS based inertial measurement unit along with a control section featuring three flip-out grid fins actuating using brushless DC electro-mechanical servomotors. With a terminal impact velocity of over 1,300 meters per second (mach 4) each PC 100 munition is capable of penetrating over 6 meters of 34 MPa (5,000 psi) reinforced concrete before exploding

by **The Technocratic Syndicalists** » Thu Jul 14, 2016 5:52 pm

RBS 96 Stormrider

General Characteristics:
Type:
Stealth Cruise Missile

Launch platform:
Aircraft

Guidance:
LADAR/IIR, INS/GPS
Physical Characteristics:
Weight:
2,300 kg

Length:
6.3 m

Diameter:
0.75 m

Warhead:
RBS 96A:
96x Fragment Incendiary Shaped Charge submunitions

RBS 96B:
40x sensor fuzed anti-armor submunitions

RBS 96C:
1,000 kg unitary penetrator
Performance Characteristics:
Propulsion:
Turbofan

Speed:
Mach 0.9

Range:
1,800 km

Overview:
The RBS 96 Stormrider is a long range, air launched, autonomous low-observable subsonic cruise missile designed by SDI Missile Systems. The RBS 96 combines a low observable airframe with a combination laser radar (LADAR) and imaging infrared (IIR) forward looking optical sensor suite along with submunitions dispenser containing either anti-material or sensor fuzed submunitions and is designed to act as an autonomous hunter-killer system for locating and destroying mobile ballistic missile and surface-to-air missile launchers deep in defended airspace. The missile is also available in a variant with a unitary earth peent rating warhead for defeating hardened and deeply buried targets..

Airframe
The Stormrider features a broad-band low-observable stealth design intended to minimize it's RCS against both high band targeting and fire control radars and low band surveillance radars when viewed from ahead or above. The stealth design is primary designed to defeat the radar systems of airborne AWACS and interceptor aircraft and concentrates the radar signature into two large spikes 90 degrees on either side of the center-line, placing the majority of the missile's radar signature into it's doppler notch. The missile features a long cylindrical fuselage with a sharp, chined nose cone along with forward-swept wings and trapezoidal tail fins intended to minimize it's frontal RCS. The control surfaces of the missiles consist of two forward swept supercritical airfoil wings, two forward swept all-moving horizontal stabilizers, and a single all-moving horizontal stabilizer which is offset from the centerline of the missile. The air inlet for the missiles' turbofan engine is a serpentine S-duct flush with the underside of the missile which hides the engine compressor blades from view by airborne radar systems. The exhaust is a flat, 2-D mixer design located underneath the fuselage which mixes the hot exhaust with ambient air to reduce the missile's infrared signature and hides the hot exhaust from view by airborne IRST (Infra-red search and track) systems from above. The skin, wings, tails, and inlets of the missile are constructed from graphite/epoxy composite and feature an embedded radar absorbing material (RAM) consisting of two layers of FeNi nanopowder coated multiwall carbon nanotubes embedded into a thermoset epoxy resin which is cured into the missile's graphite/epoxy structure. The exhaust duct of the missile is further lines with a high temperature high temperature ceramic RAM made from three-dimensional reinforced carbon/carbon (C/C) three-dimensional with embedded layers of multilayered carbon nanotubes embedded with iron nanopowder. The combination of stealth shaping and RAM results in the missile having an average frontal sector radar cross section of around -40 dBsm (0.0001 m2).

Propulsion
Name: SDI RM415
Type: Low Bypass Turbofan
Length: 750 mm
Diameter: 300 mm
Dry Weight: 65 kg
Bypass Ratio: 1:1
Compressor: 2 stage axial HPC, 1 stage centrifugal LPC
Combustor: Annular combustor
Turbine: 1 stage HPT, 2 stage LPT
Maximum Thrust: 6.3 kN
Overall pressure ratio: 14:1
Specific fuel consumption: 15 g/Kn-s
Thrust-to-Weight Ratio: 10.0:1
The Stormrider is powered by an SDI RM415 twin-spool low-bypass turbofan generating a maximum of 6.3 kN of thrust. The highly compact RM415 engine combines good fuel efficiency with a high thrust-to-weight ratio which allows the Stormrider missile to be both long ranged and highly maneuverable in flight. To reduce weight and improve efficiency the RM415 engine uses a variety of advanced composite elements including carbon fiber reinforced polyamide composite compressor blades, engine casing, and engine shafts and silicon nitride ceramic bearings, turbine blades, turbine vanes, combustor, and nozzle. The use of high temperature ceramic turbine blades removes the need for turbine blade cooling, reducing the weight and complexity of the engine. The high temperature ceramic turbine also permits a higher turbine inlet temperature, improving specific power and efficiency. Valves and fuel nozzles in the engine are constructed from 3D printed cobalt-titanium using a Direct Metal Laser Melting Machine (DMLMM) machine.

Guidance:
The RBS 96 missile is equipped with a forward-looking optical sensor suite combining a laser radar(LADAR) and imaging infrared sensor connected to a common multi-sensor signal processor (MSSP) which provides point to point midcourse guidance, target detection and automatic target recognition (ATR), submunition cueing, and low-altitude terrain following and obstacle avoidance. Both optical system share a common 20 cm diameter RC telescope with a single scanning mirror and twin raster scanning galvanometer mirrors with separate active and passive HgCdTe detector arrays. The scanning mirror gives the optical system +/- 20° azimuth and +5 to -35° elevation scanning capability. The LADAR unit consists of a CO2 laser transmitter operating at a wavelength of 10.6 μm and an active channel detector array containing a 12-element vertically oriented HgCdTe array operating in the heterodyne mode at an intermediate frequency of 70 MHz. The system operated either in pulsed mode with a 25 nsec pulse width, 20 kHz PRF, and an average transmitted power of 5W or in continuous wave (CW) mode with a 10W transmit power. The imaging infrared sensor employs the same telescope, pointing and scanning optics as the laser radar and employs a 12 element HgCdTe detector array operating in the LWIR (8-12 μm) spectrum which is pixel registered with the laser radar array in order to create composite sensor fused images which the ATR algorithms on the multi-sensor signal processor use to identify targets for the missile.

The LADAR and IIR sensors are controlled by a dynamic sensor manager that establishes search strategies, controls sensor operations, maintains and updates track files, and controls the sensor ATR algorithms. The sensor manager will use both sensors to look at each detected target where ATR results from both sensors are combined over time in an evidence accumulation process. The multi-sensor signal processor (MSSP) which processes sensor returns consists of a single instruction, multiple data (SIMD) image processor consisting of 92,0000 25 MHz 128 bit geometric arithmetic parallel processors (GAPP) which is used for 2D LADAR image and IIR image processing. A separate LADAR signal processor bank of four dual 40 MHz, 128 bit reduced instruction set computer (RISC) processors with an array of Fast Fourier Transform (FFT) co-processors which is used for 3D laser radar image processing. ATR processing for both sensors consists of sensor control and detection, multiple ATR algorithms, and multiple-level ATR fusion. The sensor manager starts by sending scanning commands to the IIR and LADAR sensors during the midcourse navigation and target search phase of the missile's mission plan. ATR processing for both sensors consists of sensor control and detection, multiple ATR algorithms, and multiple-level ATR fusion. Images from the IIR sensor are first processed with a regions algorithm to detect roads, treelines, other geographical features, and to detect target-sized regions having high thermal contrast. The LADAR sensor is then operated in a framing mode to generate a 3D angle-angle-range image or in a push broom line scan mode. In framing mode, the scanning mirror holds a fixed direction while compensating for platform motions while the raster mirrors are rastered at 10 scans per second to form an image 125 pixels in azimuth and 60 pixels in elevation. In linescan mode, the scanning mirror scans in azimuth at a rate of 2.5 scans per second and provides an image 3840 pixels in azimuth and 12 pixels in elevation with the frames formed bottom to top by scanning the nearest range first. In linescan mode the LADAR scans swathes of terrain 1.5 to 3 kilometers wide at a ground ranges up to 5 kilometers from the missile. The 3D angle-angle-range LADAR image generated is then coordinate transformed into an an orthogonal x, y, z (orthogonal) coordinate form where a duplexer module then pixel registers the LADAR image with the IIR image, assigning a thermal intensity and range value to each pixel in the image. A model based ATR algorithm is then used where detected objects in the scene similar in size to the desired targets are extracted from the imagery and matched against an onboard library of reference target models in order to determine if the detected objects are target candidates. Potential targets are then matched in a 3D mode using simultaneous x, y, and z thermal intensity, doppler, and range measurements and then declared as targets if they exceed a certain match threshold. An aimpoint vector for the target is determined by transfixing the aimpoint from the target reference model to the live object at the position of best match where the guidance system then instructs the missile to maneuver to a position and attack the target with a submunition. After all the missile's submunitions are expended the missile can kamikaze itself into a final target using the combined LADAR/IIR sensor as a seeker for terminal homing.

A strapdown INS/GPS unit in conjunction with a guidance and navigation processor defines the missiles position relative to a predetermined mission plan which consists of a series of 3D waypoints programmed into the missile before launch. The INS/GPS system consists of a tactical grade IMU containing a 6-axis ring laser gyro (RLG) based inertial measurement unit (IMU) which is combined with a 24 channel dual-frequency (L1/L2) SAASM (Selective Availability Anti-spoofing Module) based GPS receiver to provide accurate all-weather midcourse guidance for the missile. During midcourse flight the LADAR sensor is used as a laser velocimeter to input accurate missiles ground velocity data into the guidance computer. Before launch the missile is programmed with one or multiple search boxes which the missile will fly to along a set of waypoints where the missile will descend to an altitude of 500 meters AGL and flying back and forth across the search box while using its sensors to scan each search box for potential targets. The missile has the ability to search an area of 7,500 km2 at a standoff range of 1,000 kilometers, giving the missile the ability to covertly search for high value re-locatable targets deep within defended airspace. The top of the missile also contains a conformal X-band electronically steered satellite communications (SATCOM) antenna which is used to provide 2-way over-the-horizon (OTH) communications capability with the missile during flight and allows the missile's search box locations or target priority list to be updated in flight.

Warhead:

RBS 96A:The RBS 96A contains a payload of 96 SB 8 fragment incendiary shaped charge (FISC) submunitions and is intended to attack parked aircraft, lightly armored and unarmored vehicle convoys, surface-to-air missile sites, air defense radars, and other soft targets. The SB 8 submunitions are contained in 96 sideways facing launch tubes (48 per side) each containing a single submunition and a gas generator expulsion system, allowing submunitions to be individually ejected against multiple targets along either side of the weapon's flight path. Each SB 8 submunition weighs 8.2 kilograms and consists of a steel cylinder 15 centimeters in diameter and 25 centimeters long with a circumferential multiple explosively formed projectile (MEFP) warhead with 4 rows of 8 copper alloy EFP liners and a central 2.5 kg polymer bonded HMX explosive (95% HMX, 3% BDNPA/F, 3% estane) bursting charge with 4 points of initiation along the axis of the submunition. The submunition also contains three zirconium rings inside the steel casing which add an additional incendiary effect to the munition. After being ejected from the weapon each submunition is stabilized by set of spring deployed fins before deploying a parachute to slow its descent. Warhead detonated is initiated by a proximity fuze at the base of the submunition which detonates the warhead at a height of 1 meter above ground where the EFPs are ejected radially outwards at high velocity in addition to the fragments from the steel warhead case. The self-forged projectiles are designed to penetrate trucks and parked aircraft out to a range of over 15 meters where the incendiary effect of the zirconium is designed to ignite fuel which leaks from the target. The submunition also contains an impact fuze should the proximity fuze fail to function along with both electronic and electro-machinal self destruct fuzes to minimize the risk of submunitions becoming unexploded ordinance.

RBS 96B: the RBS 96B contains a payload of 40 ZEPL sensor fuzed anti-armor submunitions and is optimized for attacking convoys of armored vehicles. The submunitions are contained in 40 sideways facing launch tubes (20 per side) each containing a single submunition and a gas generator expulsion system, allowing submunitions to be individually ejected against multiple targets along either side of the weapon's flight path. Each ZEPL submunition is a cylinder 175 mm in diameter and 205 mm long with a launch weight of 18.75 kg and consists of a parachute retarding system, a tri mode active 94 GHz MMW radar/passive 94 GHz MMW radiometer/passive IR target detection sensor, and a multiple EFP warhead which is bore sighted with the target detection system. Following ejection from the weapon the ZEPL deploys a drogue parachute to slow its descent where a second vortex ring parachute then deploys which slowly spins the submunition and suspends it at approximately 30° angle from the vertical where the MMW and IR sensors scan across a decreasing spiral track beneath the submunition, scanning an area about 200 meters in diameter along the ground. The target detection sensor matches objects detected during its scan with an on-board threat-library and immediately activates the EFP warhead upon detection of a target. The EFP warhead contains a 2.0 kg polymer bonded HMX explosive (95% HMX, 3% BDNPA/F, 3% estane) charge and features a central concave tantalum liner forming the center single EFP (SEFP) which is surrounded by 16 smaller tantalum multiple-EFPs (MEFPs) which creates a shotgun-like blast of smaller EFPs to increase lethality against unarmored or lightly armored vehicles. The main SEFP has a 50 centimeter dispersion at a range of 100 meters and is capable of penetrating over 150 mm of RHA at the same distance, sufficient to punch through the roof armor of most tanks and other armored vehicles. Should the submunition fail to find a target the submunition is programmed to to self-destruct at an altitude of 10 meters, preventing it from becoming unexploded ordinance.

RBS 96C:The RBS 96C is equipped with a 1,000 kilogram hardened penetrator warhead which is designed to attack infrastructure targets such as bridges or runways as well as bunkers and deeply buried or reinforced targets. The warhead consists of a streamlined steel case 2.4 meters long and 0.37 meters in diameter constructed from 3.5 GPA tensile strength nickel-molybdenum-cobalt maraging steel (8Ni-14Mo-20Co-Fe) filled with 265 kilograms of insensitive enhanced blast explosive (50% HMX, 30% Al powder, 20% PCP/TMETN energetic binder/plasticizer). The warhead is fitted with a base mounted hard target void sensing fuze containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The detonator is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge which is armed in flight and requires a constant 500 V from the missile's power system to function. With a terminal impact velocity of Mach 0.90 to 0.95 the warhead is capable of penetrating over 4 meters of 34.5 MPa reinforced concrete before exploding. The missile's software allows for the pre-launch selection of three attack modes; a direct attack mode which flies straight into the side of the target, a pop-up maneuver followed by a terminal-dive down onto the target, or a PWD (Programmed Warhead Detonation) mode where using the missile's radar altimeters as a proximity fuze the warhead is detonated while the missile is flying directly over the target.

by **The Technocratic Syndicalists** » Mon Jul 18, 2016 10:27 pm

RBS 95 Blacksword

General Characteristics:
Type:
Anti-ship and land attack cruise missile

Launch platform:
VLS, Aircraft, TEL

Guidance:
Combined active/passive RF seeker, INS/GPS, 2-way RF datalink
Physical Characteristics:
Weight:
2,000 kg (missile), 2,400 kg (with booster)

Length:
6.3 m (missile), 7.0 m (with booster)

Diameter:
0.6 m

Warhead:
500 kg reactive fill penetrator
Performance Characteristics:
Propulsion:
Variable cycle turboramjet

Speed:
Mach 4.0 (high altitude), Mach 3.0 (sea level)

Range:
1,000 km (hi-hi-hi), 400 km (hi-lo-lo)

Overview:
The RBS 95 is a combination anti-ship and lack attack supersonic cruise missile designed by SDI Missiles & Fire Control Systems. The RBS 95 is available in three basic variants, the RBS 95S variant including missile and booster which designed to be launched from surface vessel VLS systems, the RBS 95U variant including the missile and booster inside a buoyoant capsule which is designed to be launched from submarines, and the RBS 95F variant including the missile without booster which is designed to be launched from aircraft.

Airframe
The RBS 95 missile body consists of a seeker and inlet section with mixed-compression variable geometry axisymmetric inlet cone containing terminal RF seeker and seeker electronics as well as guidance, navigation, and control (GN&C) avionics, payload section containing penetrating warhead which acts a load bearing structural member and which is surrounded by an annular air flow-through duct and concentric fuel tanks, and a propulsion section containing the missile's turbo-ramjet engine. The missile employs a Ti-22Al-25Nb titanium aluminide (TiAl) monocoque construction with stiffened titanium aluminide skin panels formed using a superplastic forming/diffusion bonding (SPF/DB) process. Aft structures of the missile including vertical stabilizers and fins are constructed from radar absorbing graphite/polyimide honeycomb sandwich composite structures with embedded polymer sheets containing ferrite and carbon black particles for radio-frequency wave absorption. The radome structure of the missile employs a reaction-sintered silicon nitride (Si3N4) structure providing high temperature resistance and low dielectric constant. Although not designed as a radar very-low observable (VLO) weapon the missile features a coating of radar absorbing paint embedded tiny ferrite spheres which combined with the other radar-absorbing structures on the missile result in an approximately 0.1 m2 frontal RCS when viewed from a 15 degree look-up angle.

Propulsion
Name: SDI RM144
Type: Turbo-ramjet
Length: 1,320 mm
Diameter: 340 mm
Dry Weight: 115 kg
Compressor: 4 stage axial
Combustor: Annular combustor
Turbine: 1 stage axial
Maximum Thrust: 32.2 kN
Overall pressure ratio: 7.8:1
Specific fuel consumption: 70 g/Kn-s
Thrust-to-Weight Ratio: 28.9:1
The missile is powered by an SDI RM144 variable cycle turboramjet engine producing a maximum of 32.2 kN of thrust which accelerates the missile from subsonic speed to its cruise speed of mach 4.0. The turboramjet engine combines a turbojet engine with a ramjet afterburner and consist of a conventional axial-flow afterburning turbojet with a variable bypass system that directly supplies inlet air to the afterburner at high mach numbers. The engine operates as an afterburning turbojet up to a speed of mach 3.0 where a series of peripheral bypass valves around the compressor face of the engine then begin to divert air around the core and directly into the afterburner. At mach 3.5 the bypass valves are fully opened and the gas generator of the turbojet engine is shut down, the engine then operating as a pure ramjet and accelerating the missile up to its design cruise speed of mach 4.0 at high altitude. Approximately 500 kilograms of JP-10 high-density synthetic jet fuel are carried by the missile in three separate fuel tanks which gives the missile a range of around 1,000 kilometers when flying a hi-hi-hi trajectory. The flow-path of the engine consists of a set of variable inlet guided vanes (VIGV), four-stage transonic axial compressor, high area ratio annual diffuser, annular vaporizer combustor, single stage axial flow turbine, ramjet afterburner, and altitude compensating variable-area plug nozzle. The compressor employs a Inconel 718 nickel-chromium superalloy case with integrally bladed rotors with low-aspect ratio blades also constructed from Inconel 718 alloy. The combustor section employs an uncooled continuous-fiber reinforced carbon-carbon ceramic matrix composite liner. The single stage turbine section uses an Inconel 188 cobalt-nickel-chromium-tungsten alloy casing with a single integrally bladed axial turbine rotor constructed from carbon-carbon composite with a designed turbine-inlet-temperature of 2200 degrees K. The rotating turbomachinery is mounted on a single shaft constructed from Inconel 718 alloy which is supported by two silicon nitride ceramic ball bearings. The ramjet afterburner section is similar to the combustion chamber and employs a Inconel 188 alloy casing with a carbon-carbon liner. The plug nozzle is also constructed from carbon-carbon composite.

Guidance & Navigation:
The RBS 95 missile employs a dual-mode seeker system which combines a multi-mode Ka band imaging radar seeker and a wideband passive radar seeker. The Ka band (34-36 GHz) imaging radar seeker is optimized for all-weather detection and engagement of surface ship and moving land targets and operates in three modes; real beam, doppler beam sharpened (DBS), and synthetic aperture radar (SAR). The real beam and DBS modes are used for wide area search while high range resolution (HRR) profiling techniques used in the real beam mode for high resolution target recognition and classification. The synthetic aperture radar (SAR) mode is used for midcourse guidance and provides high resolution imagery to refine the target classification of detected targets.

The seeker employs a digital active phased array antenna using a digital beamformer, digital MEMS phase shifters, and gallium nitride (GaN)-on-SiC T/R modules and is scanned electronically in elevation and azimuth with +/- 60° off-boresight azimuth and elevation scan capability. The seeker generates and transmits randomized low-power noise signals to detect targets, a copy of each generated randomized noise signal being stored in the seeker's active memory as to allow correlation with incoming signal returns. The high instantaneous bandwidth of the seeker (>1 GHz) combined with randomized noise signals results in extremely high range resolution and allows for both simultaneous measurement of range and doppler shift of the target. The extremely high range and doppler resolution of the seeker support clutter discrimination in littoral or other high clutter environments as well as automatic target recognition (ATR) and aimpoint selection capability. The use of a digital beamformer also enables the use of adaptive beamforming which along with super resolution algorithms enables the seeker to accurately recognize, locate, and suppress jammer sources while performing target acquisition and tracking tasks. Additional ECCM features of the seeker include low transmit power, narrow beam-width transmissions, and a dual polarized antenna to counter angle deception jamming. The passive radar seeker is mounted behind the Ka band radar seeker in the missile's nose radome and consists of a two planar spiral high band antennas and an eight element low band antenna array providing 2-40 GHz emission detection, identification, and direction finding capability which covers typical surface ship air search, navigation, and fire control radar bands. The passive radar seeker alloys the missile to approach emitting targets radar silent, only using the active radar seeker for terminal homing and target aim-point selection.

The seeker assembly is coupled with a midcourse guidance unit (MGU) which contains a 2-way satellite communications datalink and a GPS/INS autopilot system combining a 6-axis strapdown inertial measurement unit with three laser-ring gyroscopes (LRG) and three quartz resonating beam accelerometers (RBA) with a 24 channel dual-frequency (L1/L2) SAASM (Selective Availability Anti-spoofing Module) based GPS receiver. The autopilot unit provides for highly accurate 3D waypoint based terminal navigation and allows for engagement of stationary land targets using GPS grid-coordinates which can be uploaded to the missile before or after launch. Wide-area differential GPS (WADGPS) capability is supported by the autopilot's GPS system and enables impact CEPs of <3 meters when attacking geolocated land targets. Use of the two-way satellite communications datalink allows updated targeting data of moving ship targets to be sent to the missile and allows the missile to be vectored to other pre-programmed targets in flight or to be re-redirected to any other GPS grid coordinates within the missile's range. Missile health and status updated can also be transmitted back to the launch platform using the satellite datalink.

During a typical anti-ship engagement the target range and bearing information of the intended target, which can be provided either by the launch platform's sensors or by a third party, is down-linked to the missile's autopilot system. The missile is then launched and uses its autopilot to follow a series of pre-programmed 3D waypoints to guide itself to the target area. At a pre-set range from the target determined by the launch mode the missile activates its radar seeker and enters into a serpentine flight where the missile uses its passive radar seeker to scan for target emissions and its active radar seeker to search back and forth across the horizon. The seeker's track-while-scan capability enables it to detect and track multiple contacts while prioritizing targets using the seeker's automatic target recognition algorithms. Once a target has been selected the missile activates its radar altimeter and descends to sea level where it follows a sea-skimming trajectory at 5-10 meters ASL towards the target bearing. The missile can then perform additional short pop-up maneuvers to obtain better range and bearing fixes on the target and can change its trajectory to strike the target from a different direction. When approaching the target the missile performs either a terminal pop-up maneuver or follows a terminal sea-skimming trajectory while optionally performing a series of 10+ g terminal bunt and weave maneuvers, uses the imaging capability of its radar seeker to select an aimpoint on the target ship, and then impacts the top or side of the target ship where it punches through the ship's hull before exploding inside.

Warhead:
The RBS 95 missile contains a 500 kilogram reactive fill penetrating warhead which is intended for attacking both warships and extremely hardened and deeply buried land targets. The warhead is structurally integrated into the missiles' centerbody aft of the inlet and consists of a streamlined steel case 2.4 meters long and 30 centimeters in diameter constructed from 3.5 GPA tensile strength nickel-molybdenum-cobalt maraging steel (8Ni-14Mo-20Co-Fe) filled with a 125 kg high density reactive solid-fuel thermobaric explosive consisting of a cylindrical shell of solid thermobaric fuel consisting of a fuel-rich aluminum–molybdenum trioxide (Al-MoO3) metastable intermolecular composite mixture surrounding an inner cylinder of high energy density polymer bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB). When the inner explosives is detonated the warhead's steel case is ruptured and the Al-MoO3 mixture (31.6% powdered nano-Al fuel and 68.4% MoO3 oxidizer by mass) in the warhead is dispersed into the target where reflective shock waves generated by the detonation mixes the hot detonation gases with the Al-MoO3 particles, igniting and detonating the Al-MoO3 which further reacts with atmospheric oxygen to create a intense fireball and sustained (10-50 msec) blast overpressure with approximately 100% greater energy than conventional aluminized polymer bonded explosives which is capable of blowing open bulkheads and crushing walls inside the target compartment or structure. Relative to conventional solid-fuel thermobaric mixtures the presence of MoO3 oxidizer in the mixture enhances combustion efficiency and allows a sustained high pressure blast wave to be generated even in confined environments such as air-tight rooms or compartments with a limited oxygen supply. The extremely high temperature of the fireball generated from the reactive mixture (2000 to 3000° C) further adds to the destructive effect of the warhead with the ability to instantly ignite fuel, ammunition, or other flammable or explosive materials inside the target compartment or structure.

The warhead is fitted with an SDI base mounted hard target smart fuze (HTSF) containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The detonator is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge which is armed in flight and requires a constant 500 V from the missile's power system to function. The fuze supports impact velocities up to 1,200 m/s and deceleration shocks of up to 10,000 gs and is capable of counting up to 16 voids or target layers with the ability to compute a total penetration path length of up to 80 meters into the target with the ability to detonate at a programmed point within target warship or structure. When used against hard and deeply buried targets the high impact velocity of the missile allows the warhead to penetrate over 12 meters of 34.5 MPa (5,000 psi) reinforced concrete, 4 meters of 138 MPa (20,000 psi) ultra-high performance reinforced concrete, or over 60 meters of earth before exploding. Soft targets such as air defense radars or parked aircraft can also be engaged using PWD (Programmed Warhead Detonation) mode where the missile overflies the target and explodes overhead using its radar altimeter as a proximity fuze, spraying the target area with high velocity steel fragments.

by **The Technocratic Syndicalists** » Sat Oct 22, 2016 8:55 pm

Rb 100 Wyvern

General Characteristics:
Type:
Long range air-to-air missile

Launch platform:
Aircraft

Guidance:
Tri-mode active RF/passive RF/IIR, INS/GPS, 2-way RF datalink
Physical Characteristics:
Weight:
200 kg

Length:
4.0 m

Diameter:
0.3 m

Warhead:
20 kg aimable blast-fragmentation
Performance Characteristics:
Propulsion:
Triple-pulse solid fuel rocket motor

Speed:
Mach 5+

Maneuverability:
60 g

Range:
300 km

Overview:
The Rb 100 Wyvern is a long range anti-air and anti-radiation missile designed by SDI Missile Systems.

Airframe & Propulsion:
The Wyvern uses a trapezoidal lifting-body fuselage constructed from a high-temperature three-dimensional carbon fiber-PMR (polyimide) composite which combines low weight and high strength and stiffness with elevated temperature resistance compared to traditional carbon-epoxy composites. An additional layer of S-10 silicone reinforced phenolic, a charring ablator with a very low thermal conductivity, is bonded to the outside of the missile body to keep the carbon fiber-PMR fiber within its operating temperature during sustained hypersonic flight. The missile consists of five sections: a seeker section which contains the missile's tri mode seeker, a guidance section which contains the missile's guidance processor, INS/GPS unit, and thermal batteries, warhead section which contains the missile's 20 kilogram warhead and electronic safe and arm device (ESAD), propulsion section which contains the missile's triple-pulse solid rocket motor, and control section which contains the missile's control-actuation system and RF datalink antennas. The missile employs a bank-to-turn maneuvering scheme (switching to skid-to-turn mode 2 seconds before target impact for additional maneuverability) and is steered by four folding low-aspect ratio trapezoidal tail fins constructed from a phenolic composite which are actuated by high-torque electro-mechanical actuators inside the missile's tail control module.

The Wyvern is propelled by a 21 centimeter diameter triple pulse solid fuel rocket motor which employs three separate radially-burning propellant grains separated by burst disks which can each be ignited in succession at pre-programmed intervals during flight. The motor provides a peak thrust of over 35 kilonewtons and accelerates the missile to a speed of over mach 5. Each propellant grain is made from SDI's 75% HNIW, 25% GAP high performance low observable propellant with the motor containing 100 kilograms of total propellant with a 50/25/25 split between the pulses. Each propellant grain additional contains its own Nd:YAG laser laser igniter which allows for the ignition of the individual motor pulses in flight. Short delays between the pulses are used for the maximum velocity trajectory while longer intervals between pulses are used for maximum range ballistic trajectories. The motor casing is constructed from filament-wound graphite/polyimide composite with an internal aramid-filled ethylene propylene diene monomer (EPDM) insulation and external wound elastomeric insulation layers. The nozzle is made from 3D carbon-carbon composite with a titanium nozzle shell and aft enclosure which also serves to mount the missile's aerodynamic steering fins and associated electro-mechanical actuators. Control is provided by an integrated aerofin/thrust vector control (IATVC) system which integrates the packaging of the TVC system with conventional four-axis aerofin control.

Guidance & Navigation:
The Wyvern uses a SDI designed passive-active advanced all-weather seeker (PAAAWS) unit which combines an active Ka band (35 GHz) radar seeker, wide-band (0.5 - 40 GHz) passive radar seeker, and a mid-wave imaging infrared seeker. After being fired by the launching aircraft in the general direction of the target the missile uses the passive radar seeker to silently search for and home in on the target's radar or radio emissions. If no emissions are detected the missile is programmed to briefly switch on its own radar seeker and conduct a search for a target. If a target is found another short active radar sweep is done a few seconds later to get speed and heading information and to confirm the target's identity through the automatic target recognition (ATR) functionality of the radar seeker. The missile then flies to the computed "kill zone" where it then homes in the target using sensor fusion of the IIR and active radar seeker, the use of both radar and imaging infrared imaging for terminal being intended to make the missile extremely resilient to electronic countermeasures and active decoys deployed by the target. Midcourse guidance is provided by a 6-axis SDI TNS 450 tactical-grade timing and inertial measurement Unit (TIMU) which combines three milli-Hemispherical Resonator Gyroscope (mHRG) and three quartz resonating beam accelerometers (RBA) in a low SWaP package (500 cc volume, <1.0 kg mass, <5 watts max power consumption) package which provides <0.0003°/√hr gyro angle random walk and < 0.0001 °/hr bias stability performance. The IMU is coupled to an SDI designed GPS spatial temporal anti-jam receiver (GSTAR) unit with wide area differential GPS (WADGPS) capability providing <1 meter resolution 3-dimensional position accuracy in flight. A 2-way RF datalink operating in the L band connected to a software defined radio (SDR) is also fitted to the missile which allows guidance updates from the launch aircraft to be sent to the missile and flight and for weapon impact assessment (WIA) information including real time missile status, location and target information to be sent back to the launch aircraft in flight.

The radar seeker consists of a Ka band (35 GHz) active electronically-scanned array (AESA) seeker assembly which is housed in a broadband ceramic radome constructed of reaction-sintered silicon nitride (Si3N4). The Ka band seeker employs a digital beamformer, digital MEMS phase shifters, and a planar array of GaN (Gallium Nitride) on diamond monolithic microwave integrated circuit (MMIC) T/R modules and power amplifiers and is capable of scanning +/- 60 degrees off boresight in both azimuth and elevation. The millimeter-wave Ka band seeker provides an extremely high angular resolution for target tracking and discrimination and features over 1 GHz of instantaneous bandwidth for increased ECM resistance. The use of a digital beamformer also enables the use of adaptive beamforming which along with super resolution algorithms enables the seeker to accurately recognize, locate, and suppress jammer sources while performing target acquisition and tracking tasks. ECCM features of the seeker include frequency-modulated continuous-wave (FMCW) operation to minimize probability of detection by enemy receivers, high instanenous bandwidth, dual-polarized aperture, randomized burst transmissions, active sidelobe cancellation, and home-on-jam (HOJ) functionality.

The passive seeker assembly consists of of a total of 12 conformal, ultra-wideband (XWB) antennas placed radially around the missiles forward fuselage behind the seeker assembly which provide 360 degree detection of radar signals in the 500 MHz to 40 GHz range (UHF - Ka Band). The 12 antennas feed into a photonic receiver unit with >40 GHz of instanatnous bandwidth and provides accurate detection, classification, and angle of arrival (AoA) information of incident radar waves and allows the missile to passively home in on emitting aircraft or ground based radars without the use of its active radar seeker. When used as an anti-radiation missile the missile can operate in four modes; direct mode, area suppression mode, or self-protect mode. In direct mode, which is primarily intended for attacking stationary emitters, the missile is launched an emitter with a known range and bearing where the missile flies a minimum time-of-flight trajectory to engage the target in as short a time as is possible. In area suppression mode, which is intended for attacking mobile SAM systems, maritime targets, and AEW aircraft, the missile is programmed to fly toward a specific area at high altitudes and then dive towards the target area while searching for a specific target or targets programmed before launch. In self protect or reactive mode, which is intended to engage pop-up emitters at short to medium ranges in a 360 degrees aspect around the aircraft, the missile is launched towards a target detected by the aircraft's RWR/ECM system and after launch will immediately turn and fly directly towards the target emitter bearing until the missile is able to acquire it with its own seeker.

The infrared seeker assembly consists of a 256 x 256 pixel imaging infrared (IIR) seeker mounted on a 2-axis gimbal for pointing and stabilization which provides the seeker with +/- 90 degree field of view capability. The IIR seeker employs an InGaAs (indium gallium arsenide) nBn type high-operating-temperature (HOT) staring focal plane array (FPA) detector array which operates in the MWIR (3-5 µm) band. A micro-Integrated dewar cooler assembly with miniature stirling cooler is used to keep the high-operating-temperature (HOT) detector at a temperature of 120K, higher than the 77K required of traditional cooled IR detectors and reducing the sight, weight, and power consumption of the cooling unit. The infrared seeker is mounted in a sapphire dome in the nose of the missile which is actively cooled by a dome cooling system (DCS) using argon gas pumped through micro channels in the sapphire dome window. The dome is protected during hypersonic cruise by a cover which is ejected during the terminal homing phase where the IR seeker will immediately begin autonomous target search mode. During IR seeker homing the missile is programmed to maintain a positive angle-of-attack and a positive attitude relative to the target to ensure it stays within the FOV of the infrared seeker.

Warhead & Fuzing:
The Wyvern contains a 20 kilogram aimable blast-fragmentation warhead which has the ability to concentrate its lethal effects in the direction of the target. The warhead consists of an pre-fragmented cylinder constructed from reactive tungsten shrapnel cubes surrounding a cylindrical polymer-bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB) charge. The pre-fragmented cylinder is surrounded by twelve radial strips of additional PBX which can each be independently detonated. When the warhead is fuzed the charges facing the strips on the side facing the target are detonated, causes the pre-fragmented case to flatten in the direction of the target. The main charge inside the case and the line charges on the opposite side of the target direction are then detonated, causing the fragments in the flattened part of the case to be ejected in the direction of the target at extremely high velocity. The reactive shrapnel is made from a PTFE/Aluminum/Tungsten (82.5% W, 10% PTFE, 7.5% Al) alloy which is inert under normal conditions but unlike regular shrapnel will explode and burn when subjected to the stress of hypervelocity impact with a solid object. Detonation of the warhead is controlled by a guidance integrated fuzing (GIF) system which uses target angle and velocity measurements from the missile's radar seeker and imaging infrared seeker to adaptively fuze the warhead. High resolution target range and bearing information from the radar seeker and bearing information from the MWIR infrared seeker is used to provide real-time predictions of time and position of target intercept in the warhead plane in order to compute optimum warhead initiation time to minimize miss distance. The position and distance measurements of the target in the warhead plane at the predicted time of intercept are used to set the direction and spread of fragments from the missile's aimable warhead before the warhead is fuzed.

by **The Technocratic Syndicalists** » Mon Jan 30, 2017 9:34 pm

RBS 83 Arbalest

General Characteristics:
Type:
Stealth Cruise Missile

Launch platform:
VLS

Guidance:
INS/GPS, PTAN, IIR
Physical Characteristics:
Weight:
1,750 kg (missile), 2,150 kg (with booster)

Length:
6.3 m (missile), 7.0 m (with booster)

Diameter:
0.6 m

Warhead:
480 kg tandem charge warhead
[/list]
Performance Characteristics:
Propulsion:
Turboprop

Speed:
Mach 0.85

Range:
3,700 km

Overview:
The RBS 83 Arbalest is an ultra-long range, surface launched, low-observable subsonic cruise missile designed by SDI Missile Systems. The RBS 83 is intended for precision strikes on high value targets including airfields, radar stations, and hardened and deeply buried targets and consists of a low observable airframe, propfan propulsion system, INS/GPS, terrain reference, and image based navigation system, and a tandem warhead system capable of defeating both hardened fixed and area targets.

Airframe
The RBS 83 missiles features a low-observable stealth design intended to minimize it's RCS primarily against airborne and surface based X band targeting and fire control radars. The missile features a long hexagonal shaped fuselage with a chined nose cone intended to minimize it's frontal RCS. The air inlet for the missiles' turbofan engine is a serpentine S-duct flush with the underside of the missile which hides the engine compressor blades from view by airborne radar systems. The exhaust is a flat, 2-D mixer design located at the rear of the fuselage which mixes the hot exhaust with ambient air to reduce the missile's infrared signature and hides the hot exhaust from view by airborne IRST (Infra-red search and track) systems from above. The missile is constructed primarily vacuum assisted resin transfer molding (VARTM) graphite/epoxy composite and feature an embedded radar absorbing material (RAM) coating consisting of two layers of FeNi nanopowder coated multiwall carbon nanotubes embedded into a thermoset epoxy resin which is cured into the missile's graphite/epoxy structure. The exhaust duct of the missile is further lines with a high temperature high temperature ceramic RAM made from three-dimensional reinforced carbon/carbon (C/C) three-dimensional with embedded layers of multilayered carbon nanotubes embedded with iron nanopowder.

Propulsion
Name: SDI TPM360
Type: Three-shaft Propfan
Length: 750 mm
Diameter: 300 mm
Dry Weight: 65 kg
Bypass ratio: 35:1
Compressor: 2 stage axial LPC, 1 stage centrifugal HPC
Combustor: Annular combustor
Turbine: 1 stage HPT, 1 stage LPT, 6 stage FPT
Maximum Thrust: 5.0 kN
Overall pressure ratio: 20:1
Specific fuel consumption: 10 g/Kn-s
Turbine inlet temperature: 1,430 °C
Thrust-to-Weight Ratio: 8.0:1
The RBS 93 missile is powered by an SDI TPM360 propfan engine which produces up to 5 kN of thrust. Tge TPM is a three-spool counter rotating propfan engine consisting of a two stage axial low pressure compressor, single stage centrifugal high pressure compressor, annular combustor, single stage high pressure turbine, single stage low pressure turbine, and a counter-rotating six stage free powerturbine which directly drives two rows of counter-rotating propfan blades which rotate at 10,000 RPM with a design tip speed of 180 m/s. The propfan engine employs an 8x8 fan blade arrangement with two rows of 8 thin, highly swept propeller blades made from 4D carbon fiber/epoxy composite. The propfan blades are hinged at their base, allowing them to fold for storage inside the missile launch canister.

The TPM360 includes a dual-channel full authority digital electronic control system (FADEC) with control modes including independent control of blade pitch and propeller speed allowing variable synchrophasing control of each propfan engine to minimize engine noise and vibration, protective measures for regulating turbine-inlet temperature and preventing inadvertent engine overspeed or overtorque, and fault modes allowing for propellor blade feathering and gas generator compressor/turbine section windmilling if an engine fails or has to be shut down in flight. The FADEC control system is housed in a dual-channel electronic control unit containing circuitry connected to various engine sensors whose inputs are used by the FADEC system to control fuel flow, propeller pitch, variable compressor vanes and stators, bleed air flow, and other systems to optimize the performance of the engine throughout the missile's flight envelope.

Guidance:
The Arbalest features a tri-mode guidance and navigation system which combines INS/GPS guidance with a precision terrain aided navigation (PTAN) system and image based navigation using a imaging infrared (IIR) seeker. The missile's INS/GPS unit consists of an SDI TNS 570 tactical inertial measurement unit and a GPS receiver system. The TNS 570 is an enhanced 6-axis resonator fiber optic gyro (RFOG) based tactical inertial measurement unit designed by SDI Missile Systems and consists of three resonator fiber optic gyros and three monolithic quartz structure vibrating beam accelerometers contained a compact, low SWaP (750 cc volume, <1.5 kg mass, <10 watts max power consumption) package which provides aircraft gyrcocompass based performance with <0.003°/√hr gyro angle random walk and <0.1 °/hr bias stability in a tactical munition IMU size form factor. The TNS 570 IMU is coupled to a 48 channel dual-frequency (L1/L2) SAASM (Selective Availability Anti-spoofing Module) based GPS receiver with M-Code compatibility and >90 dB J/S digital anti-jamming capability. The GPS system employs twin controlled reception pattern antennas (CRPAs) with adaptive beam steering and directional nulling capability located on either side of the missiles's tail control section which along with ionosphere correction capability provided simultaneous L1/L2 operation provides the weapon with <2 meter position accuracy in heavy GPS jamming environments.

The INS/GPS system is augmented by a precision terrain aided navigation (PTAN) system, an evolved form of TERCOM (Terrain Contour Matching), which provides highly accurate in-flight midcourse guidance without reliance on satellites or external signals. The missile is equipped with three C band (6.0 to 6.4 GHz), solid-state, low probability of intercept (LPI) interferometric synthetic aperture radar altimeters blended into the underside of the missile which provide highly accurate digital maps of the terrain below the missile in flight. The radar imagery is then compared with a <3 meter resolution digital terrain elevation data (DTED) map which allows the missile's in flight location to be determined within 3 meters accuracy. Low transmit power of the radar altimeters and use of spread-spectrum, frequency modulated continuous waveform (FMCW) operation minimize the risk of missile detection by hostile ECM systems.

The INS/GPS and PTAN systems are further augmented by a cooled 512 x 512 element InSb imaging infrared (IIR) seeker operating in the MWIR (3– 5 µm) band which is mounted in the nose of the missile behind a facteted optical window. The seeker has a 10° instantaneous field of view and is mounted to a 2-axis stabilized gimbal system driven by twin limited angle torque motors (LTA) which gives the seeker +/- 30° pointing capability both in elevation and in azimuth. The IIR seeker is used to provide mage based navigation capability and can navigate using up to 20 predefined terrain waypoints along its route. The seeker is also used for terminal homing where the missile compares a stored image of the target taken from high-resolution satellite imagery with the actual target image as seen by the missile seeker itself. CEP with the IIR seeker is <1m and <3m with pure INS/GPS guidance.

Warhead:
The RBS 83 missile carries a 480 kg tandem charge warhead intended primarily for destroying bunkers, reinforced structures, bridges, dams, and other hard targets. The tandem charge warhead consists of a 80 kilogram shaped charge 36 cm in diameter and 54 cm in length with an aluminum liner containing 45 kilograms of polymer bonded HMX explosive (95.5% HMX, 4.5% estane and 5702-Fl plastic binder) and a 400 kilogram follow through bomb consisting of a streamlined 2.75 GPA (400,000 psi) tensile strength nickel-molybdenum-cobalt maraging steel (13Ni-10Mo-15Co-Fe) case 24 cm in diameter and 230 cm long containing 75 kilograms of insensitive polymer bonded thermobaric explosive (50% HMX, 30% Al powder, 20% PCP/TMETN energetic binder/plasticizer). The follow-through warhead is fitted with a base mounted SDI hard target smart fuze (HTSF) containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes which can be selected to optimize the warhead effect based on expected target depth and hardness. The fuze is capable of counting up to 16 voids or hard layers and calculating a total penetration path length of 78 meters. The detonator inside the fuze is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge which is armed in flight and requires a constant 500 V from the missile's power system to function. With a missile impact velocity of 300 m/s the tandem charge warhead of the RBS 87 is capable of penetrating 30 to 40 meters of soil or 4 to 5 meters of 34 MPa (5,000 psi) reinforced concrete at impact angles between 30° and 90°. The warhead is designed to operate in three modes; airburst mode using the missile's radar altimeter as a proximity fuze for use against are targets including parked aircraft and fixed surface-to-air missile batteries, an impact detonation mode uses against unreinforced above ground structures, and a penetration mode using the layer and void-counting capability of the smart hard target fuze for use against concrete bunkers or below ground targets.

by **The Technocratic Syndicalists** » Mon Jan 30, 2017 9:45 pm

Rb 80 Rattlesnake

General Characteristics:
Type:
Short-medium range air-to-air missile

Launch platform:
Aircraft

Guidance:
Imaging Infrared (IIR), INS/GPS, RF datalink
Physical Characteristics:
Weight:
90 kg

Length:
2.9 m

Diameter:
170 mm

Warhead:
10 kg blast/fragmentation
iPerformance Characteristics:
Propulsion:
Dual-pulse solid fuel rocket

Speed:
Mach 4.0+

Maneuverability:
60 G

Operational Range:
50 km

Overview:
The Rb 80 is a short and medium range air-to-air missile designed with a large diameter rocket motor providing extremely high acceleration, combination aerodynamic and thrust-vector control for extreme maneuverability, and dual-band imaging infrared seeker with long acquisition range and high off boresight capability.

Airframe & Propulsion:
The Rb 80 missile consists of four sections; guidance section with high off boresight imaging infrared (IIR) seeker and active optical target detector, warhead section with electronic safe and arm device (ESAD) and blast-fragmentation warhead, rocket motor section, and rear control actuation section with tailfin actuators and gimballed TVC nozzle system. The 16 centimeter diameter rocket motor provides a peak thrust of over 100 kN and employs SDI minimum-smoke insensitive tactical propellant consisting of 25.5% GAP energetic binder, 4.5% TMETN (trimethylolethane trinitrate) plasticizer, 58.5% ADN (ammonium dinitramide) oxidizer, and 11.5% HMX (Octogen) combining high isp and burn rate, low impact and thermal sensitivity, and low exhaust signature. The motor casing is constructed from laminated transformation induced plasticity (TRIP) maraging steel providing extremely high structural strength and high temperature resistance. Aerodynamic control is provided by four tail fins actuated by compact electro-mechanical servomotors and a hydraulically actuated omni-axis gimballed nozzle with 20 degree gimbal angle. The wingless design gives the missile low drag at supersonic speed while the tail control unit and thrust-vector control system give the missile up to 100 g of lateral acceleration capability, 120° angle-of-attack capability, and a turn rate of up to 100° per second.

Guidance
The Rb 80 missile is equipped with a nose mounted 512 x 512 pixel dual-band HgCdTe (mercury cadmium telluride) starring focal plane Array (FPA) imaging infrared (IIR) seeker operating in both the the MWIR (3-5 μm) and LWIR (8-14 μm) bands. An onboard Stirling cycle cryocooler fed from an onboard nitrogen bottle maintains seeker temperature at 80 degrees K during flight. The infrared FPA is mounted to a two-axis stabilized gimbal system providing +/- 120° azimuth and elevation field of view and allowing for high off bore-sight (HOBS) targeting. The seeker logic employs dual-band contrast lock functions which fuse the MWIR and LWIR outputs from the seeker to provide reliable target detection and tracking capability against high speed, aggressively maneuvering targets and against small, low altitude targets in the presence of ground clutter. The guidance section of the missile is also equipped with a strapdown, low SWaP (size, weight, area, and power) tactical grade IMU containing 3-axis fiber-optic gyro (FOG) and 3-axis solid-state silicon accelerometers which are combined with a SAASM based GPS receiver to provide midcourse phase guidance for the missile.

The Rb 80 supports both lock-on before launch (LOBL) and lock-on-after-launch (LOAL) modes with optional 3rd party targeting and in-flight datalink targeting capability. When used in LOBL mode the missile's seeker can be queued and locked onto a target by the pilot's helmet mounted sight or display (HMS/HMD) or by the aircraft's IRST, radar, or passive ESM sensors. In LOAL mode the missile can be launched at targets outside its passive seeker range by feeding in target azimuth or azimuth and range data from the aircraft's IRSt, radar, or ESM sensors. Third-party targeting by other airborne platforms is also supported for attacking targets not within sensor range of the launch platform and a 2-way RF datalink integrated into the missile allows for mid-course guidance updates to be sent to the missile by the launch platform when used against longer range beyond visual range (BVR) targets. When mounted externally the missile can also be used as an infra-red search and track system by displaying video feed from the seeker in the cockpit's head-down display or to the pilot's head mounted display (HMD).

Warhead
The Rb 80 missile contains a 10 kilogram deformable blast-fragmentation warhead which has the ability to concentrate its lethal effects in the direction of the target. The warhead consists of an pre-fragmented cylinder constructed from heavy metal tungsten alloy (HMTA) surrounding a polymer-bonded explosive (88% HMX, 12% HTPB) charge. The pre-fragmented cylinder is surrounded by twelve radial strips of additional polymer-bonded explosive which can each be independently detonated. When the warhead is fuzed the charges facing the strips on the side facing the target are detonated, causes the pre-fragmented case to flatten in the direction of the target. The main charge inside the case and the line charges on the opposite side of the target direction are then detonated, causing the fragments in the flattened part of the case to be ejected in the direction of the target at extremely high velocity. Fuzing is via an active optical target detector (AOTD) laser proxmity fuze in the mid section of the missile or an impact fuze in the nose behind the seeker.

by **The Technocratic Syndicalists** » Tue May 16, 2017 10:40 pm

Rb 81 Archer

General Characteristics:
Type:
Tactical ballistic missile

Launch platform:
TEL

Guidance:
INS/GPS
Physical Characteristics:
Weight:
1,700 kg

Length:
6.1 m

Diameter:
0.56 m

Warhead:
RBS 81A:
8x terminally guided submunitions (TGSM)

RBS 81B:
16x AM101 wide area mines

RBS 81C:
500 kg blast-fragmentation
Performance Characteristics:
Propulsion:
Solid fuel rocket

Speed:
Mach 6.0 (1,800 m/s) burnout

CEP:
<3 m

Range:
400 km

Overview:
The Rb 81 Archer is a tactical ballistic missile designed by SDI which is launched from SDI's RS-90 Firestorm mobile rocket artillery system.

Airframe & Propulsion:
The Archer missile consists of four sections; guidance section, warhead section, propulsion section, and control section. The guidance section houses the missile's inertial navigation sensor, GPS receiver, digital autopilot, and internal communications systems. The warhead section consists of a thin 7075 aluminum shell with internal load-bearing structure and front and rear bulkheads which contains the missile's submunition payload. A central tube runs between the bulkheads and acts as a wiring tunnel through the warhead section. The warhead section contains a skin severance system which uses a series of linear shaped charges to blow off the skin panels and release the missile's submunition payload. The propulsion section contains the missile's solid fuel rocket motor which consists of a graphite-epoxy motor case, composite modified double- base propellant, insulation/liner, phenolic nozzle insert, and an igniter arm/fire assembly. The control section is located around the nozzle at the rear of the missile and contains four electro-mechanical actuators used to actuate the missile's four rear mounted control fins.

Guidance
The Archer missile is guided by a 6-axis ring-laser gyro based inertial system and a GPS system with a 24 channel dual-frequency Selective Availability Anti-spoofing Module (SAASM) based GPS receiver, and a guidance & navigation computer which gives the missile a range-independent CEP of under 3 meters. The missile's autopilot operates in attitude mode during the missile's boost phase and switches to an acceleration mode after rocket motor burnout. After launch the missile performs a 90° roll maneuver to orient itself in the proper roll direction which it maintains for the rest of the flight. The Archer does not fly a pure ballistic trajectory and is programmed to make a series of rapid and erratic turns and course corrections on the way to its target.

Warhead
Rb 81A: The Rb 81A is designed primarily to attack columns of armored vehicles and contains a payload of eight terminally guided submunitions (TGSMs) surrounding a central air bag dispenser system. At an altitude of around 1,000 meters the missile's flight computer detonates a pair of of linear shaped charges running along the sides of the warhead section which cut open the aluminum skin panels of the warhead section where the airbags are then activated, expelling the submunitions from the missile. Each TGSM is 140 mm in diameter and 900 mm long with a weight of 20.0 kilograms and consists of a front seeker section with gimballed 2-axis stabilized dual-mode 94 Ghz millimetric wave (MMW) radar and 128 x 128 pixel LWIR (8 – 12 µm) imaging infrared (IIR) seeker and impact fuze, guidance electronics section with inertial measurement unit (IMU), control electronics unit, and precursor warhead, warhead section with electro-mechanical safe & arm device (ESAD) and main shaped charge warhead, and rear tail control unit with thermal battery, air data sensor, deployable tail steering fins and electro-mechanical control actuation system. The TGSM employs a shaped charge warhead with a forward precursor warhead employing a two-layered molybdenum liner designed to defeat explosive reactor armor (ERA) and a main shaped charge warhead employing a copper liner capable of penetrating over 1,100 mm of RHA after ERA. After being deployed from the missile each TGSM deploys its four rear rear tailfins to stabilize itself and then deploys a set of midbody fabric wings and performs a pull-up maneuver and enters a constant altitude glide towards the target area. While gliding towards the target area each TGSM scans back and forth across a ground track 1 to 2 kilometers wide with its radar seeker and uses high range resolution (HRR) radar processing and high resolution SAR mapping to detect and image both moving and stationary targets. When the seeker's automatic target recognition (ATR) algorithms identify a tank or other armored target the submunition steers towards the target and then descends in a terminal dive, impacting the top of the target where its shaped charge warhead detonates on impact.

Rb 81B: The Rb 81B carries a payload of 16 AM101 Spider wide-area anti tank mines and is intended to complement the Rb 81B by creating anti-tank minefields deep behind enemy lines. Each AM101 mine is 380 mm long, 180 mm in diameter, weighs 16 kg, and consists of a cylindrical fiberglass body with eight deployable spring-loaded legs containing a seismo-acoustic target detection device (TDD), submunition with gas generator ejection system, and a 2-way radio communications system. The mines are carried in two rows of six mines and one row of four mines surrounding a central air bag dispenser system. At an altitude of around 1,000 meters the missile's flight computer detonates a pair of of linear shaped charges running along the sides of the warhead section which cut open the aluminum skin panels of the warhead section where the airbags are then activated, expelling the mines from the missile. Each mine then descends to the ground using a parachute where on impact the mine's spring-loaded legs are deployed to stand the landmine upright where the mine is then armed and begins searching for targets. When the mine's seismo-acoustic sensor array detects an approaching vehicle within a range of 100 meters the mine turns toward the direction of the target, elevates to the correct firing angle, and launches a sensor fuzed submunition with an explosively formed penetrator (EFP) warhead at the target using a gas generator inside the mine body. After being launches the submunition deploys an extendable fabric samara wing to stabilize itself and spins while searching for the target with a combination passive multi-band infrared (IR) and active LADAR (Laser Radar) sensor. When a target has been detected the submunition fires a multiple-EFP (MEFP) warhead consisting of a central 450 gram tantalum EFP surrounded by a ring of 16 smaller tantalum EFPs. The main EFP can penetrate 150 mm of RHA at a distance of 150 meters while the 16 smaller EFPs create a shogun-like blast of fragments effective against soft targets.

Rb 81C: The Rb 81C contains a 500 kg penetrating blast-fragmentation warhead and a multi-functional fuze with impact, impact plus delay, and proximity fuzed airburst modes. The 500 kilogram warhead consists of a a streamlined low-carbon alloy steel case filled with 125 kilograms of shock and temperature insensitive polymer bonded explosive filler consisting of 65% RDX, 15% HTPB, and 20% aluminum.

by **The Technocratic Syndicalists** » Sat Jun 03, 2017 10:58 pm

Rb 94 Lance

General Characteristics:
Type:
Hypervelocity anti-tank guided missile

Launch platform:
Ground Vehicles

Guidance:
Side-Scatter Laser Beam Riding
Physical Characteristics:
Weight:
50 kg

Length:
1.5 m

Diameter:
0.15 m

Warhead:
5 kg depleted uranium penetrator
Performance Characteristics:
Propulsion:
Dual-pulse solid fuel rocket

Speed:
Mach 6 (2,000 m/s)

Range:
0.4-8 km

Overview:
The RBS 94 Lance is a ground vehicle launched hit-to-kill hyper-velocity anti-tank guided missile (HVATGM) designed to defeat modern main battle tanks (MBTs) at extended ranges on the battlefield.

Airframe & Propulsion:
The Lance missile consists of three sections, the nose section containing depleted uranium penetrator rod and guidance electronics, motor section containing the missile's dual-pulse solid-fuel rocket motor and solid attitude control motors, and nozzle section containing the missile's nozzle and flip-out stabilization fins. The dual-pulse motor features twin radially burning grains with a wagon-wheel grain configuration made from an extremely high burning rate, insensitive, minimum smoke HNF/GAP based propellant containing 75% HNF (hydrazinium nitroformate) and 25% GAP (glyzidyl azide polymer). Each propellant grain is separated by a burst disk and each provides approximately 130 kN of thrust for <0.6 seconds after ignition. The motor features a transverse wound carbon-fiber-reinforced polyetheretherketone (CFR-PEEK) construction with an internal aramid-filled ethylene propylene diene monomer (EPDM) insulation and an external sacrificial kevlar overwrap to protect the motor case from the extreme thermal loads experienced during hypersonic flight near sea level. The motor nozzle is constructed from 3-D carbon-carbon (C-C) ceramic matrix composite. Instead of control fins the missile is steered using a series of 108 small attitude control motors (ACMs) located in the ogive section of the missile which are used to steer the missile in flight. The attitude control motors are constructed using a wound graphite/epoxy case and a TZM (titanium-zirconium-molybdenum) alloy nozzle insert and each provide 50 N-s of impulse with a peak thrust of 6 kN. The ACMs are commanded by a motor fire circuit connected via a flexprint circuit to each ACM which is encapsulated within the inner core of the missile forward body which also contains the guidance processor unit and the missile's inertial measurement unit.

Guidance:
The Lance missile employs a side-scatter laser beam riding guidance system which uses a FLIR detector and an off-axis 1.06-μm laser designator from the launch platform to deliver guidance updates to the missile in flight. The missile contains four recessed rectangular shaped side-looking optical windows placed 90 degrees apart on the missile's midbody each with a 90 degree field of view which are used to indirectly receive guidance information via atmospheric scattering of the laser beam emitted by the launch vehicle's laser designator. After the launch vehicle has detected a target it illuminates the target with its 1.06-μm laser designator then launches the missile and uses a FLIR with auto-target tracking functionality to track the target and continuously illuminate it with its 1.06-μm laser designator. The laser designator is programmed to project a circular beam pattern around the missile with a scan rate of 75 Hz which is sequentially stepped down in size as the missile approach the target. The four optical windows around the missile's centerbody are designed to detect the laser beam as it sweeps around the missile and send guidance updates to the missile's autopilot to keep the missile centered in the circular guidance beam as it flies towards the target. With the side-scatter laser beam riding method the laser beam is not required to directly illuminate the missile, preventing the laser beam from potentially being obscured by the exhaust of the missile's rocket motor. To keep the missile stable in flight the missile employs an autopilot system with 6-axis MEMS inertial measurement unit (IMU) designed to survive the >1000 g launch acceleration of the missile.

by **The Technocratic Syndicalists** » Sun Jun 04, 2017 12:57 am

RBS 87 Corvus

General Characteristics:
Type:
Cruise Missile

Launch platform:
Aircraft

Guidance:
INS/GPS, PTAN, IIR
Physical Characteristics:
Weight:
1,200 kg

Length:
4.3 m

Diameter:
0.7 m

Wingspan:
2.5 m

Warhead:
480 kg tandem charge warhead

Performance Characteristics:
Propulsion:
Turbofan

Speed:
Mach 0.95

Range:
1,000 km

Overview:
The RBS 87 Corvus is a low observable air launched land attack cruise missile designed by SDI Missile Systems which is designed to destroy high-value, well-defended, hardened targets from significant standoff distances.

Airframe
The RBS 87 missile consists of a semi-monocoque trapezoidal cross section fuselage with a pointed nose constructed from foam-core graphite/epoxy sandwich panels supported by an internal stainless steel strongback and multiple internal aluminum alloy bulkheads. The upper fuselage contains two folding launch lugs which are used to attach the missile to a hardpoint or rotary launcher mounted ejector rack. The nose of the fuselage contains the missile's imaging infrared (IIR) seeker, proximity fuze, air data probe, missile guidance unit (MGU), inertial measurement unit (IMU), GPS receiver, and precursor warhead. The central fuselage contains the follow through warhead and wraparound center fuel tank, a submerged air inlet on the underside of the fuselage, and a top mounted umbilical connector and safe separation sensor. The aft fuselage contains the missile's turbofan engine, aft fuel tank, a top mounted anti-jam GPS antenna, and the vertical and horizontal tail control actuation system. The missile's two wings are constructed from graphite/epoxy composite and are stored folded in the upper aft fuselage and are pyrotechnically deploying at launch. The missile's control surfaces consist of two all-moving horizontal tails and a single ventral vertical tail which fold up against the aft fuselage and like the wings are pyrotechnically deployed after launch.

Propulsion
Name: SDI RM170
Type: Low bypass turbofan
Length: 940 mm
Diameter: 305 mm
Dry Weight: 66 kg
Compressor: 2-stage fan, 2-stage axial LPC, 1-stage centrifugal HPC
Combustor: Annular combustor
Turbine: 1 stage HPT, 2 stage LPT
Maximum Thrust: 4.0 kN
Overall pressure ratio: 14:1
Turbine inlet temperature: 1,090 °C
Bypass ratio: 1:1
Specific fuel consumption: 30 g/Kn-s
Thrust-to-Weight Ratio: 6.2:1
The RBS 87 is powered by an SDI RM170 miniature turbofan engine rated at 4.0 kN maximum continuous thrust. The RM170 is a twin spool turbofan engine with a 1:1 bypass ratio and features a low pressure spool with a two stage fan with with 17-4 precipitation hardened stainless steel fan blisks and two stage axial flow powder-metal compacted titanium alloy low pressure compressor (LPC) driven by an uncooled two stage IN713LC alloy low pressure turbine (LPC) and a high pressure spool with a single stage centrifugal powder-metal compacted titanium high pressure compressor driven by a single stage cooled IN100 alloy high pressure turbine. The combustor is an annular flow-throw design and burns JP-10 synthetic jet fuel supplied by a centrifugal fuel spray nozzle.

Guidance:
The RBS 87 features a tri-mode guidance and navigation system which combines INS/GPS guidance with a precision terrain aided navigation (PTAN) system and image based navigation using a imaging infrared (IIR) seeker. The INS/GPS system consists of a tactical grade IMU containing a 6-axis ring laser gyro (RLG) based inertial measurement unit (IMU) which is combined with a 24 channel dual-frequency (L1/L2) SAASM (Selective Availability Anti-spoofing Module) based GPS receiver to provide accurate all-weather midcourse guidance for the missile. The INS/GPS is augmented by a precision terrain aided navigation (PTAN) system, an evolved form of TERCOM (Terrain Contour Matching), which provides highly accurate in-flight midcourse guidance without reliance on satellites or external signals. The missile is equipped with three C band (6.0 to 6.4 GHz), solid-state, low probability of intercept (LPI) interferometric synthetic aperture radar altimeters blended into the underside of the missile which provide highly accurate digital maps of the terrain below the missile in flight. The radar imagery is then compared with a <3 meter resolution digital terrain elevation data (DTED) map which allows the missile's in flight location to be determined within 3 meters accuracy. Low transmit power of the radar altimeters and use of spread-spectrum, frequency modulated continuous waveform (FMCW) operation minimize the risk of missile detection by hostile ECM systems.

The INS/GPS and PTAN systems are further augmented by a cooled 256 x 256 element InSb imaging infrared (IIR) seeker operating in the MWIR (3– 5 µm) band which is mounted in the nose of the missile behind a faceted low-observable optical window. The seeker has a 10° field of view and is mounted to a 2-axis stabilized gimbal driven by twin limited angle torque motors (LTA) which gives the seeker +/- 30° pointing capability both in elevation and in azimuth. The IIR seeker enables image based navigation and can navigate using up to 20 predefined terrain waypoints along its route. The seeker is also used for terminal homing where the missile compares a stored image of the target taken from high-resolution satellite imagery with the actual target image as seen by the missile seeker itself. CEP with the IIR seeker is <1m and <3m with pure INS/GPS guidance.

Payload:
The RBS 87 missile carries a 480 kg tandem charge warhead intended for destroying bunkers, reinforced structures, bridges, dams, and other hard targets. The tandem charge warhead consists of a 80 kilogram shaped charge 36 cm in diameter and 54 cm in length with an aluminum liner containing 45 kilograms of polymer bonded HMX explosive (95.5% HMX, 4.5% Estane and 5702-Fl plastic binder) and a 400 kilogram follow through bomb consisting of a streamlined 2.75 GPA (400,000 psi) tensile strength nickel-molybdenum-cobalt maraging steel (13Ni-10Mo-15Co-Fe) case 24 cm in diameter and 230 cm long containing 100 kilograms of insensitive polymer bonded thermobaric explosive (50% HMX, 30% Al powder, 20% PCP/TMETN energetic binder/plasticizer). The follow-through warhead is fitted with a base mounted SDI hard target smart fuze (HTSF) containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The fuze is capable of counting up to 16 voids or hard layers and calculating a total penetration path length of 78 meters. The detonator inside the fuze is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge which is armed in flight and requires a constant 500 V from the missile's power system to function. With a missile impact velocity of 300 m/s the tandem charge warhead of the RBS 87 is capable of penetrating over 5 meters of 34 MPa (5,000 psi) reinforced concrete before denoting its charge inside the structure.

by **The Technocratic Syndicalists** » Sun Jun 04, 2017 1:12 am

RBS 97 Arclight

General Characteristics:
Type:
Hypersonic boost-glide missile

Launch platform:
Submarine VLS

Guidance:
INS/GPS
Physical Characteristics:
Weight:
10,400 kg

Length:
12.0 m

Diameter:
1.0 m

Warhead:
500 kg unitary penetrator
Performance Characteristics:
Propulsion:
2-stage solid-fuel rocket

Speed:
Mach 15 (5.0 km/s) burnout

Range:
5,000 km

Overview:
The RBS 97 Arclight is an advanced submarine launched hypersonic boost-glide missile intended to attack heavily defended time-sensitive and/or hard and deeply buried targets (HDBTs) deep inland with a high probability of penetrating air defense systems and successful reaching and destroying its target. The missile employs a maneuvering boost-glide re-entry vehicle with large cross-range capability and flies a non-ballistic depressed trajectory to minimize detection range by hostile air defense and early-warning radar systems.

Airframe & Propulsion:
The RBS 97 Arclight is a two-stage solid-fuel missile employing filament wound graphite/epoxy motors with high-performance composite modified double base propellant. The first stage motor is 1.0 meters in diameter, 6.2 meters long, has a gross mass of 6,200 kg with 5,700 kg of propellant and burns for 35 seconds and provides 228.50 kN of peak thrust with a vaccum specific impulse of 270 s. The second stage motor is 1.0 meters in diameter, 2.5 meters long, has a gross mass of 2,900 kg with 2,600 kg of propellant and burns for 25 seconds with a peak thrust of 76.0 kN and a vacuum specific impulse of 290s. Both first and second stage motors feature graphite/epoxy wound motor cases and employ a high energy solid propellant with a 90% solid loading consisting of 20% aluminum, 24% HMX, 46% AP, and 10% HTPB. The throat and nozzle of each motor is constructed from triaxially braided 3-D carbon-carbon composite with motor motor stages feature gimballed thrust-vector control using an electrohydraulic actuated ball nozzle joints providing +/- 7.5°thrust vectoring on both stages. The missile employs a boost glide re-entry vehicle (BGRV) with a biconic shape and a spherical blunted tip. The vehicle is steered using four rear mounted HfB2–SiC ultra-high-temperature ceramic composite fins with hydraulically actuated trailing elevons to provide roll, pitch, and yaw control during the atmospheric portion of flight along with an aft mounted hypergolic reaction control system which provides roll, pitch, and yaw between BGRV separation and atmospheric reentry. The body of the reentry vehicle structure is constructed from Ti-6Al-4V titanium alloy and features a hafnium carbide (HfC) coated tape wrapped carbon phenolic heatshield with a 3-D carbon/carbon nosecone which is bonded to the underlying titanium structure with pyrolytic graphite supports which keeps the underlying titanium structure within its temperature limits during extended hypersonic flight through the atmosphere.

Guidance:
The reentry vehicle is guided in flight through a combination GPS/INS system which combines a radiation hardened strategic-grade inertial measurement unit with a Selective Availability Anti-spoofing Module (SAASM) based GPS receiver system. The INS system is used during the initial phase of flight when the vehicle is subjected to plasma blackout conditions, transitioning to hybrid GPS/INS navigation later in flight as the plasma cloud around the vehicle dissipates. The INS system employs SDI's Strategic Inertial Measurement Unit, a strapdown strategic grade inertial measurement unit employing 3-axis laser-ring gyro (LRGs) and 3-axis pendulous integrating gyroscopic accelerometer assemblies. The INS system is coupled to a GPS receiver with four dual frequency (L1/L2) wideband GPS antenna blended into the rear surface of the reentry vehicle

Warhead
The reentry vehicle contains a structurally integrated 500 kilogram penetrating blast-fragmentation warhead whose thick steel casing acts as both a forward load bearing support and a heat sink for the boost-glide reentry vehicle. The warhead has a streamlined steel case 2.4 meters long and 30 centimeters in diameter constructed from 3.5 GPA tensile strength nickel-molybdenum-cobalt maraging steel (8Ni-14Mo-20Co-Fe) filled with a 125 kg high density reactive solid-fuel thermobaric explosive consisting of a cylindrical shell of solid thermobaric fuel consisting of a fuel-rich aluminum–molybdenum trioxide (Al-MoO3) metastable intermolecular composite mixture surrounding an inner cylinder of high energy density polymer bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB). When the inner explosives is detonated the warhead's steel case is ruptured and the Al-MoO3 mixture (31.6% powdered nano-Al fuel and 68.4% MoO3 oxidizer by mass) in the warhead is dispersed into the target where reflective shock waves generated by the detonation mixes the hot detonation gases with the Al-MoO3 particles, igniting and detonating the Al-MoO3 which further reacts with atmospheric oxygen to create a intense fireball and sustained (10-50 msec) blast overpressure with approximately 100% greater energy than conventional aluminized polymer bonded explosives which is capable of blowing open bulkheads and crushing walls inside the target compartment or structure. Relative to conventional solid-fuel thermobaric mixtures the presence of MoO3 oxidizer in the mixture enhances combustion efficiency and allows a sustained high pressure blast wave to be generated even in confined environments such as air-tight rooms or compartments with a limited oxygen supply. The extremely high temperature of the fireball generated from the reactive mixture (2000 to 3000° C) further adds to the destructive effect of the warhead with the ability to instantly ignite fuel, ammunition, or other flammable or explosive materials inside the target compartment or structure.

The warhead is fitted with an SDI base mounted hard target smart fuze (HTSF) containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The detonator is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge which is armed in flight and requires a constant 500 V from the missile's power system to function. The fuze supports impact velocities up to 1,200 m/s and deceleration shocks of up to 10,000 gs and is capable of counting up to 16 voids or target layers with the ability to compute a total penetration path length of up to 80 meters into the target with the ability to detonate at a programmed point within target warship or structure. When used against hard and deeply buried targets the high impact velocity of the missile allows the warhead to penetrate over 12 meters of 34.5 MPa (5,000 psi) reinforced concrete, 6 meters of 138 MPa (20,000 psi) ultra-high performance reinforced concrete, or over 60 meters of earth before exploding. Soft targets such as air defense radars or parked aircraft can also be engaged using PWD (Programmed Warhead Detonation) mode where the missile overflies the target and explodes overhead using its radar altimeter as a proximity fuze, spraying the target area with high velocity steel fragments.

Flight Sequence:
Before launch the missile's navigation system is activated and the specified mission trajectory is loaded onto the missile's flight computer. On launch a gas generator in the missiles' launch capsule is ignited, generating high pressure gas which ejects the missile from its launch canister. The missile's first stage motor is then ignited and burns for 35 seconds, accelerating the missile to a velocity of around 2.5 km/s. Following first stage burn the second stage is ignited and burns for a further 25 seconds, accelerating the missile to a final burnout velocity of around 5.0 km/s (Mach 15) at an altitude of around 60,000 meters at a distance of around 250 kilometers downrange. Following second stage burn the nose fairing is jettisoned and the missies' guidance system activates the thrust termination system, opening a series of six equally spaced ports at the top of the rocket motor, dropping the pressure inside the second stage motor and generating a reverse-thrust which decelerates the second stage motor and allows it to separate from the boost-glide reentry vehicle. Following separation from the second stage the BGRV then orients itself using it's INS and uses its hypergolic reaction control system (RCS) to maneuver and position itself for atmospheric reentry. Following atmospheric reentry at distance of around 1,500 kilometers downrange the BGRV dives down to an altitude of 40,000 meters to gain speed before performing a pull-up maneuver to establish an optimal angle of attack before beginning its several thousand kilometer range hypersonic glide towards the intended target. After gliding to the intended target area the vehicle performs a series of roll-reversal maneuvers to decrease its speed to approximately 1,300 m/s where the vehicle then performs a high-G pull-down maneuver from its final glide altitude of around 35,000 meters and dives down sharply towards its intended target, impacting at a velocity of approximately 1,000 m/s.

by **The Technocratic Syndicalists** » Mon Jun 05, 2017 6:55 pm

RBS 90 Hornet

General Characteristics:
Type:
Miniature loitering cruise missile

Launch platform:
Aircraft

Guidance:
Tri mode millimeter wave (MMW), imaging infrared (IIR), and semi-active laser (SAL) seeker, 2-way RF datalink, GPS/INS
Physical Characteristics:
Weight:
65 kg

Length:
2.0 m

Diameter:
0.18 m

Warhead:
8 kg multi-mode EFP
Performance Characteristics:
Propulsion:
Turbojet

Speed:
Mach 0.9

Ceiling:
10,000 m

Range:
500 km

Overview:
The RBS 90 Hornet is a long range, high endurance, miniature swarming cruise missile system designed by SDI Missile Systems. The Hornet is intended primarily to attack armored vehicle columns, self propelled artillery systems, and relocatable air defense and ballistic missile systems and combines a small, low RCS airframe with airbreathing turbojet propulsion, a tri-mode seeker with ATR (Automatic Target Recognition) capability, swarm networking system, and a multi-mode EFP warhead effective against both armored and unarmored targets.

Airframe & Propulsion
Name: SDI RM55
Type: Turbojet
Length: 305 mm
Diameter: 145 mm
Dry Weight: 5.9 kg
Compressor: 1-stage centrifugal
Combustor: Annular combustor
Turbine: single stage
Maximum Thrust: 450 N
Overall pressure ratio: 6:1
Turbine inlet temperature: 1,260 °C
Specific fuel consumption: 28 g/Kn-s
Thrust-to-Weight Ratio: 7.8:1
The Hornet is powered by an SDI RM55 micro turbojet engine producing 450 N of thrust at sea level. Designed to be an expendable engine for small missiles and target drones RM55 is a single-spool turbojet with a single stage mixed-flow compressor and single stage turbine supported by a pair of ceramic bearings with a rated spool speed of 130,000 RPM. The single stage mixed-flow compressor consists of a machined impeller with 8 blades and a single row axial diffuser with 16 machined vanes. The compressor is driven by a single stage uncooled turbine constructed from hot isostatically pressed reaction-bonded silicon nitride(Si3N4). The engine is fueled using J9 high-density synthetic jet fuel which also acts to cool and lubricate the internal engine components and thus eliminating the need for a separate oil system.

Guidance:
The Hornet missile features a tri-mode seeker combining a millimeter wave (MMW) active radar, passive imaging infrared (IIR) detector, and semi-active laser (SAL) sensor into a common aperture. The millimeter wave radar seeker is a W band (94 GHz) frequency-modulated continuous-wave (FMCW) seeker which is effective against land and sea targets in all weather conditions and in the presence of battlefield obscurants. The radar seeker employs a combination of high-resolution range profile (HRRP) and doppler beam sharpening (DBS) enhanced high-resolution burst-SAR mode to image both moving and stationary targets detected by the seeker for automous target recognition purposes. The imaging infrared (IIR) seeker is a 640 x 480 pixel uncooled detector which operates in the long-wave infrared spectrum (8 to 12 µm) and provides passive day and night detection of moving and stationary vehicle targets. The semi-active laser (SAL) sensor is co-located with the infrared detector aperture and allows either the launch platform or a forward observer to designate targets with a 1.06 µm laser designator which the missile can then attack. The missile is intended to be launched at targets not directly visible to the launch aircraft where the missile is then programmed to search for targets autonomously with its seeker. Three targeting modes are supported by the weapon; point attack, column attack, and area attack. For communicating between missiles the Hornet uses a wireless local area network (WLAN) based swarm networking system using a 4 watt S band (2.4 GHz) RF datalink with a 2 Mb/s channel data transmission rate.

Point Attack: In point attack mode a single missile is programmed to search a given target area defined by the launch aircraft for a specific target. After launch the missile performs a flyout to the designed target area where the missile then climbs or descends to a programmed search altitude and activates its seeker which sweeps back and forth across the ground track corresponding to the ground search area defined before launch. When the desired target is acquired the missile is programmed to perform a terminal dive down onto the target, striking its more vulnerable top armor. If the seeker does not detect the target in the defined search area the missile is programmed to fly to a designated self destruct point outside of the target search area before self destructing.

Column Attack: In column attack 3 to 12 missiles are fired at a column of tanks or other vehicles with each missile fired attacking the nth target. The mode is similar to point attack mode is except the missile search area is programmed to correspond to the approximate length and width of a vehicle column which has been detected by an airborne or space based radar sensor. The first missile which enters the search area is programmed to attack either the first or last vehicle it detects, the second missile then attacking the second or second-to-last target, etc, until all vehicles in the column have been attacked and destroyed. The automatic-target-resolution capability of the seeker allows for soft-skinned vehicles in the column of tanks to be ignored is so desired.

Area Attack: In area attack mode 3 to 12 missiles are programmed to search and attack a programmed target area containing multiple target vehicles. This mode is also similar to point attack mode but uses a much larger search area corresponding to a dispersed battlefield target such as a tank company or surface-to-air missile site. In area attack mode each missile will be programmed to search an area within the larger target area, attacking the nth target it detects until all targets within the search area have been engaged.

Warhead & Fuzing:
The Hornet is equipped with an 8.0 kilogram multi-mode selectable explosively formed penetrator (EFP) which is intended to attack both armored and unarmored targets at extended standoff ranges. The warhead is 17 centimetres in diameter and consists of a central concave tantalum cone, 2.5 kg of polymer bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB), central and peripheral detonators, and aluminum electro-mechanical safe & arm device (ESAD) housing, The EFP warhead is capable of being fired in three modes including long rod penetrator, aerostable slug, and directed fragmentation mode depending on target type and aspect. For attacking tanks and other armored targets the long rod penetrator mode is used which maximizes armor penetration capability with over 500 mm of RHA defeat capability while being aerostable at ranges up to 50 meters. For attacking tanks and and other armored targets from the top aspect and from longer standoff ranges the aerostable slug mode is used which forms a slug like projectile designed to maintain aerostability for longer ranges. The aerostable slug, although not having as much penetration as the long rod penetrator penetrator, has enough penetrating power to defeat the top armor of most tanks with over 170 mm of RHA defeat capability at a range of 100 meters. For attacking soft targets the directed fragmentation mode which causes the tantalum liner to break up into shrapnel which is projected towards the target area like a large shotgun blast.

by **The Technocratic Syndicalists** » Tue Jun 06, 2017 11:30 pm

GB 1000

General Characteristics:
Type:
Guided glide bomb

Launch platform:
Aircraft

Guidance:
IIR, INS/GPS, 2-way RF datalink
Physical Characteristics:
Weight:
1,300 kg

Length:
4.0 m

Diameter:
0.4 m

Finspan:
1.5 m

Warhead:
1,000 kg unitary bomb

Performance Characteristics:
CEP:
<3 m

Range:
160 km (12,000 meter altitude release)

Overview:
The GB 1000 is a family of modular electro-optic/infrared+INS/GPS guidance and control kits which can convert various 1,000 kilogram bomb bodies into precision guided weapons.

Design & Airframe:
The GB 1000 weapon consists of five sections: front mounted seeker and guidance module with electro-optical/infrared seeker fuze, control module with autopilot, thermal battery, and GPS receiver, forward warhead adapter, warhead, rear warhead adapter with pivoting wing section, and tail assembly with rear tailfins and electro-mechanical control actuators.

Guidance
The GB 1000 employs an uncooled imaging-infrared focal plane array seeker contained in an injection-molded polymer housing in the nose of the weapon. The 320 x 240 pixel uncooled microbolometer array used by the seeker operates in the LWIR (7 to 13.5 µm) band and features a +/- 5° azimuth and +/- 5° elevation field of view. The imaging infrared seeker is coupled with an INS/GPS guidance system located in the rear of the weapon which contains a 6-axis ring laser gyro (RLG) based inertial measurement unit (IMU) and a 12 channel dual-frequency Selective Availability Anti-spoofing Module (SAASM) based GPS receiver unit which provides highly accurate all-weather midcourse and terminal phase weapon guidance.

Before launch the GPS gird coordinates of the target are determined and an image of the target taken from satellite, UAV, or reconnaissance aircraft imagery or by the launch platform's own synthetic aperture radar (SAR) or forward looking infrared (FLIR) sensors is selected and a desired aim-point on the target image specified either before flight or in flight by the pilot or WSO (Weapon Systems Officer) using a Head-Down Display (HDD) in the cockpit. The GPS grid coordinates of the target are downlinked to the weapon's autopilot and the image of the target with desired aimpoint is downlinked to the bombs seeker before the weapon is released. When the aircraft comes within weapon glide range of the intended target the weapon is released and glides toward the target area using INS/GPS midcourse guidance with the ability to follow a 2D or 3D route via series of 3D waypoints in order to avoid enemy defenses or other obstacles. During this phase the 2-way RF datalink can be used to specify one of the alternate targets, transmit imagery of a new target, or direct the bomb to strike an alternate set of GPS grid coordinates along its route instead. Once over the target area the weapon is programmed to nose over and dive down towards the target area with the terminal dive angle variable from a shallow glide into the targets side or a near vertical dive from above for penetrating hardened and/or deeply buried targets. In the final 2,000 meters of flight the imaging infrared seeker is activated and images the target area, comparing the seeker imagery with the downloaded target image to both positively identify the target and desired aimpoint. Once the infrared seeker has locked onto the target the infrared seeker to IMU alignment error is calculated to within 100 microradians and the weapon's INS/GPS guidance system is updated with the correct position, the bomb then pulling up to several Gs if necessary to align itself with the correct trajectory before impact. Terminal impact can be one of two modes, a shallow glide into the side of the target or a diving strike from above with a terminal angle-of-attack selectable If the imaging infrared seeker is unable to identify or locate the target due to weather conditions or other reasons the weapon will simply follow INS/GPS guidance all the way to impact. The CEP of the weapon is less than 1 meter with the imaging infrared seeker or less than 3 meters when using solely INS/GPS guidance.

Warheads:

SD 1000 General Purpose: The SD 1000 is a general purpose bomb combining high explosive blast and fragmentation effects. The bomb consists of a streamlined low-carbon alloy steel case filled with 475 kilograms of shock and temperature insensitive polymer bonded explosive consisting of 65% RDX, 15% HTPB, and 20% aluminum. The bomb is used with nose and base mounted fuzes providing for either instantaneous or 0.010, 0.025, 0.050, 0.100, or 0.250 second impact plus delay fuzing. When used with impact fuze mode the bomb is capable of creating craters 15 meters in diameter and up to 10 meters deep and can project lethal fragmentation in a 400 meter radius from the impact point of the weapon. When used with delay fuze modes the bomb is capable of penetrating 1 meter of 34 MPa (5,000 psi) reinforced concrete before exploding.

PC 1000G Unitary Penetrator: The PC 1000G is a hardened penetrator bomb designed to destroy heavily reinforced or buried structures. The bomb consists of a 3.5 GPA (500,000 psi) tensile strength nickel-molybdenum-cobalt maraging steel (8Ni-14Mo-20Co-Fe) sub-caliber penetrating warhead 2.4 meters long and 0.37 meters in diameter fitted with an outer aluminum sheet metal casing which gives the bomb the same outer aerodynamic shape as the SD 1000 bomb. On impact the outer aluminum casing breaks off, allowing the inner steel warhead to penetrate into the target before exploding. The warhead is filled with 265 kilograms of enhanced blast thermobaric explosive (50% HMX, 30% Al powder, 20% PCP/TMETN energetic binder/plasticizer) which is initiated by a base mounted hard target void sensing fuze (HTVSF) containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The detonator is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge. With a terminal impact velocity of near mach 1 when used with a high altitude release the PC 1000 warhead is capable of penetrating up to 4 meters of 34 MPa (5,000 psi) reinforced concrete before exploding.

PC 1000HTB Agent Defeat Weapon: The PC 1000HTB is a variant of the PC 1000 hardened penetrator bomb which carries a two-stage high-temperature incendiary fill and a payload of thermally fuzed grenade bomblets designed to destroy chemical and biological weapon storage facilities. The warhead contains a 300 kilogram high-temperature incendiary (HTI) fill contained in a row of seven canisters which along with a payload of eight thermally fuzed grenades are ejected from the base of the warhead at a predetermined point inside the target structure using the warhead's base mounted hard target void sensing fuze (HTVSF). At the predetermined expulsion point inside the target the MEMS accelerometer in the void sensing fuze is used to determine the munitions forward velocity and a series of linear shaped charges are detonated tp separate the tail assembly and aft warhead bulkhead from the warhead. The microprocessor in the fuze then initiates a multi-charge expulsion system in the nose of the warhead with four explosive charges sized on a base two system which allows for up to fifteen selectable ejection velocities, the fuze selecting the ejection velocity which closest matches the penetrator's forward velocity in order to ensure the incendiary fill and thermally fuzed grenades are deposited in the right layer of the structure.

The incendiary fill is contained in seven metal canisters which each consist of a central core consisting of a thin-walled steel tube containing a polymer bonded explosive charge which is surrounded by an annulus containing titanium-boron intermetallic fuel along and lithium perchlorate oxidizer in a polychlorotrifluoroethylene (PCTFE) binder. The central core of each canister also contains a time fuze which activates upon canister expulsion from the warhead, triggering the high explosive charge in the central core which ignites and disperses the incendiary fill throughout the structure. Upon initiation the titanium and boron first react to form titanium diboride which then reacts again with the lithium perchlorate oxidizer to form titanium oxide, lithium boron oxide, and lithium chloride. The two-stage reaction is extremely violent and burns at a temperature of 3,600° C to 3,900°C, releasing an enormous amount of heat which causes the interior of the structure to rapidly heat up to several hundred degrees C. The high temperature of the reaction also causes the lithium chloride and polychlorotrifluoroethylene to disassociate and produce large amounts of monatomic chlorine and monatomic fluorine along with hydrochloric and hydrofluoric acid which act as a biocide to defeat biological warfare agents.

The eight thermally fuzed grenades are deposited into the structure along with incendiary fill and are initiated by a thermal fuze which activates when the ambient temperature has reached 260°. Each grenade has a mass of 2.4 kg and consists of the thermal fuze which is attached to a thermally insulated cylindrical steel body 100 cm in diameter and 150 cm long containing 3 rows of 3 copper alloy explosively formed projectile (EFP) liners surrounding a central 0.59 kilogram polymer bonded HMX explosive (95% HMX, 3% BDNPA/F, 3% estane) charge with 3 points of initiation along the axis of the grenade. Each grenade also includes a spring-loaded self-righting mechanism consisting of eight strip steel legs which activates after landing to ensure each grenade remains upright before initiation. Upon detonation each grenade projects a total of nine EFPS radially which are intended to penetrate metal tanks and containers inside the structure containing biological or chemical agents. the agents that spill out then being immediately neutralized by the heat and biocides released by the incendiary fill. Also packaged with the bomblets in the back of the warhead is a fill of calcium hypochlorite dihydrate, a biocide agent which serves to neutralize any biological agents should the warhead penetrate into a container or storage tank containing a biological agent before the high temperature incendiary fill of the warhead can be deployed.

SA 1000 Fuel-Air Explosive: The SA 1000 is a fuel-air explosive (FAE) bomb which produces blast and thermal effects effective against targets such as reinforced structures, vehicles, parked aircraft and exposed personnel. The SA-1000 bomb consists of a thin fiberglass casing filled with 735 kilograms of ethylene oxide fuel and two polymer bonded explosive bursting charges. The first bursting charge ruptures the casing of the bomb and releases the ethylene oxide fuel as an aerosol cloud which then mixes with the surrounding atmospheric oxygen. A second detonating charge ignites the aerosol cloud several milliseconds later, creating an extremely powerful blast wave which flattens all objects in close proximity to the epicenter of the detonation. When using the SA 1000 warhead the nose section of the GB 1000 is fitted with a radar altimeter which is used to detonate the bursting charge of the SA 1000 warhead at a predetermined altitude over the target.

by **The Technocratic Syndicalists** » Sun Jun 18, 2017 11:51 pm

RBS 91 Copperhead

General Characteristics:
Type:
Fiber-optic guided missile

Launch platform:
Ground vehicle, ship

Guidance:
imaging infrared (IIR), INS/GPS, fiber-optic datalink
Physical Characteristics:
Weight:
45 kg

Length:
2.0 m

Diameter:
0.18 m

Warhead:
9 kg multi-purpose shaped charge
Performance Characteristics:
Propulsion:
Turbojet

Speed:
200 m/s

Range:
0.5 - 60 km

Overview:
The RBS 91 Copperhead is a long range fiber-optic guided missile designed to attack and destroy armored and unarmored vehicles, bunkers, helicopters and other battlefield targets. The missile features an imaging infrared (IIR) seeker for all-weather target acquisition which is coupled with a fiber-optic guidance wire which unrolls behind the missile in flight and allows the gunner to manually fly and target the missile from a control station inside a vehicle or warship.

Airframe & Propulsion:
Name: SDI RM70
Type: Turbojet
Length: 330 mm
Diameter: 170 mm
Dry Weight: 3.5 kg
Compressor: 6-stage axial
Combustor: Annular combustor
Turbine: Single stage
Maximum Thrust: 470 N
Overall pressure ratio: 3.4:1
Specific fuel consumption: 44 g/Kn-s
Thrust-to-Weight Ratio: 5.1:1
The Copperhead missile features a cylindrical S2 glass/epoxy filament-wound composite fuselage which is divided into four sections; the seeker section which contains the imaging infrared (IIR) seeker, cryogenic seeker coolant bottle, and precusor warhead, the warhead section which contains the main charge and electro-mechanical safe & arm device (ESAD), the integrated propulsion module (IPM) section which contains the missile's RM70 turbojet engine, inlet and exhaust ducts, fuel pump, fuel tank, and igniter cartridge, the guidance section which contains a 6-axis inertial measurement unit (IMU), laser alimeter, and GPS receiver, and the fiberoptic datalink section with contains the reel-out fiber optic guidance wire. Lift is provided by four flip-out wings with a span of 1.4 meters while control is provided by four electro-mechanically actuated tail control fins which fold for storage inside a launch canister. The missile does not use a solid rocket booster and is instead "soft-launched" from its canister using its turbojet engine whose thrust during launch is boosted by around 25% over its maximum cruise thrust using a methanol injection system with thrust-vector control (TVC) during boost provided by four moveable fins in the turbojet exhaust nozzle.

Guidance:
The Copperhead uses a 640 x 480 pixel platinum silicide (PtSi) focal plane array seeker mounted to a dual axis gyro-stabilized gimbal which is designed to provide all-weather day-and-night detection and identification of battlefield targets. The seeker operates in the MWIR band (3 to 5 μm) and is cooled to 80K using a nitrogen bottle contained inside the seeker section. The seeker has two selectable fields' of view including a 5.0° x 3.75°NFOV and a 10° x 7.5° WFOV and is mounted to a servomotor driven two-axis gimbal which allows the seeker to be steered +/- 30°in both azimuth and elevation. Midcourse guidance is provided by a naunit in the missile guidance section which includes a MEMS-based inertial measurement unit with 3-axis hemispherical resonator gyroscope (HRG) and 3-axis piezoelectric quartz accelerometer, 24-channel SAASM (Selective Availability Anti-spoofing Module) based GPS receiver, digital autopilot computer, and a laser altimeter. The rear of the missile contains a fiber-optic bobbin which 240μm diamater fiber-optic cable which spools out behind the missile and links it with the control station on the firing platform. The fiber-optic cable has a maximum data transfer rate of 200 MBs and serves to transmit the video feed of the seeker to the control station and transmit control signals from the control station to the missile and unlike radio based datalink system provides the missile with immunity to active jamming and other forms of electromagnetic interference.

The guidance system of the Copperhead allows for both automatic or man-in-the-loop guidance modes. After launch the Copperhead is programmed to pitch over at an altitude of 400 meters where it then follows a constant-altitude cruise with a nominal cruise speed of 125 m/s towards the target area. In automatic mode the missile can be programmed to follow up to several hundred GPS waypoints along a pre-programmed route while the missile's seeker scans back and forth across the missile's ground track with a stepped-stair search to detect and home in on potential targets. During flight missile can be switched to manual operation mode where the gunner steers the missile with a joystick and can use the video feed from the infrared seeker to search for and acquire targets. When flying the missile manually mode the wide field-of-view (WFOV) mode is used to search for and aquire targets after which the gunner uses the narrow field-of-view (NFOV) mode for target identification and to lock the missile onto the target which is done by centering the crosshairs on the gunner's display with the desired target.

Warhead:
The Copperhead missile is equipped with an 8 kilogram multi-mode tandem shaped-charge (HEAT) warhead combing blast-fragmentation and shaped-charge effects which is effective against both armored and unarmored vehicles and structure targets. The main warhead consists of an HF-1 high-fragmenting steel case containing 5.7 kilograms of polymer-bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB), copper shaped charge liner, syntactic foam wave-shaper, central and peripheral detonators, and aluminum electro-mechanical safe & arm device (ESAD) housing. A precursor warhead employing a two-layered molybdenum shaped charge liner and containing 1.0 kilograms of HMX based polymer-bonded explosive, is located ahead of the main warhead in the seeker section of the missile and serves to defeat any explosive reactive armor (ERA) tiles on the target before the main warhead detonates. When used against armored vehicles the impact fuze is used and the warhead is detonated using the peripheral detonators which creates a high speed, small diameter penetrating jet capable of penetrating in excess of 1,500 mm RHA after ERA. For attacking soft targets a proximity fuze in the nose of the missile can be used which allows the warhead to air-burst, the main warhead being initiated with the central and peripheral detonators which cause the warhead's copper shaped charge liner and high-fragmentation steel case to break up and release over 9,000 high-velocity fragments, creating a lethal-zone to exposed personnel over 40 meters in diameter

by **The Technocratic Syndicalists** » Sat Jul 29, 2017 4:16 pm

BR 30 Viper

General Characteristics:
Type:
Air-to-ground rocket

Launch platform:
Helicopter, aircraft

Guidance:
Semi-active laser homing (SALH)
Physical Characteristics:
Weight:
15.2-21.7 kg kg

Length:
1,610-1,980 mm

Diameter:
81 mm

Warhead:
4.5 kg HEAT or 11 kg blast/fragmentation
Performance Characteristics:
Propulsion:
Solid fuel rocket

Speed:
520-820 m/s

Operational Range:
12 km

Overview:
The Viper is an 81 mm diameter fin-stabilized guided rocket with shaped charge and high explosive warheads which are effective against both point and area targets. The Viper can be launched from a variety of pods capable of being mounted to rotary and fixed wing aircraft and housing either 4, 6, 12, or 22 rockets.

Airframe & Propulsion:
The Viper rocket consist of three sections, guidance section with semi-active laser seeker, fuze, and steering canards, warhead section with either shaped charge or blast fragmentation warhead, and common rocket propulsion unit with rocket motor and rear stabilization fins. The rocket motor section weighs 8.7 kilograms and consists of a transversely wound glass/epoxy motor case which contains a radial burning insensitive minimum-smoke PGA/TMETN/ BTTN/RDX based extruded cross-linked double-base (XLDB) solid fuel propellant grain with a boron potassium nitrate (BKNO3) pyrotechnic igniter along with nozzle section with wrap-around fins. The rocket motor provides 13.2 kN of peak thrust and burns for 0.7 seconds, accelerating the rocket to a burnout velocity of 520 to 820 m/s dependent on warhead weight. The rear fin section of the propulsion unit has four fins curved to match the outside diameter of the rocket fuselage which flip out sideways to open. The nozzle additionally contains a set of flutes which impart a spin to the rocket as it fires to provide additional stabilization.

Warhead
The Viper is available with two interchangeable payload sections: a 4.5 kilogram shaped-charge (HEAT) warhead with an impact fuze designed to engage armored vehicle targets and an 11 kilogram high explosive blast-fragmentation (HE-FRAG) warhead with a combined impact, delay, and proximity fuze for engaging structures and soft targets such as unarmored vehicles or personnel. The HEAT warhead weighs 4.5 kilograms and contains a copper liner and 1.0 kilograms of octol explosive (75% HMX 25% TNT) and is capable of penetrating in excess of 450 mm of RHA. The HE-FRAG warhead weighs 11 kilograms and and features an HF-1 high fragmenting steel alloy case containing 3.1 kilograms of polymer bonded explosive (88% HMX and 12% HTPB). On detonation the HE-FRAG warhead releases over 2,000 high velocity steel fragments lethal to exposed personnel within a 50 meter radius.

by **The Technocratic Syndicalists** » Sat Jul 29, 2017 7:17 pm

RBS 98 Kestrel

General Characteristics:
Type:
Anti-Tank Guided Missile Launcher

Guidance:
Laser Beam Riding
Physical Characteristics:
Weight:
9.8 kg launch tube, 6.0 kg CLU

Length:
870 mm

Rocket Diameter:
140 mm

Warhead:
2.3 kg top attack EFP
Performance Characteristics:
Propulsion:
Two-stage solid fuel rocket

Speed:
300 m/s

Operational Range:
40 - 2,500 m

Overview:
The RBS 98 is a man portable top-attack anti-tank guided missile system designed to engage and destroy main battle tanks and and other armored fighting vehicles at combat ranges up to 2.5 kilometers. The weapon is small and light enough to be carried by a single soldier and gives individual soldiers the ability to engage and destroy heavily armored vehicles at typical combat ranges. The complete FGM-198 system consist of reusable command launch unit (CLU) and expendable launch tube assembly (LTA) containing the missile.

Command Launch Unit:
The command launch unit or CLU is the reusable targeting component of the system which is attached to the launch tube assembly before firing. The CLU weighs 6.0 kilograms and contains a second generation mercury cadmium telluride (HgCdTe) long-wave thermal (8 – 14 µm) imager with staring focal-plane array (FPA), a daylight CCD camera, eye-safe 2.1 μm holmium laser rangefinder, and 10.6 μm CO2 laser designator. The long-wave infrared imager features a 4X magnification wide field-of-view (WFOV) mode and 12X magnification narrow field-of-view (NFOV) mode while the daylight CCD camera features a fixed 4x magnification. Both thermal imager and CCD camera feature electronic auto-focus, 2-D image stabilization, and automatic target tracking (ATT) capability to allow for more effective target acquisition and engagement. A linear drive cryocooler contained in the CLU is used to keep the temperate of the focal plane array (FPA) of the infrared imager at around 70-100 degrees K. The CO2 laser designator is part of the laser beam-riding guidance system and produces an overlapping group of conical laser beams which are detected by a laser receiver on the tail of the missile which then steers the missile towards the operator's aimpoint where the laser designator beams intersect. The CO2 laser illuminator includes a variable focal length lens which decreases the diameter of the laser beam as the missile approaches the target to minimize the probable miss distance at the target. The CLU is powered by a rechargeable lithium-ion battery which give the CLU a battery life of around 16 hours before it needs recharging.

Missile:
The RB 98 missile is 140 mm in diameter, 850 mm long, and weighs 6.4 kg at launch (9.8 kg with its launch tube). The missile has a cylindrical body with four rear mounted flip-out fins for steering and stabilization which spring out as the missile is launched from the tube. The front of the missile features a blunted dome-like nose which contains a combined laser/magnetic target detection device (TDD) which is used to detect the target vehicle and trigger detonation of the top attack EFP warhead. The tail of the missile contains a laser receiver which is designed to measure the missile's deviation from the laser beam emitted by the CLU's CO2 guidance laser and sends steering commands to the missile's inertial autopilot based on the deviation from the guidance beam. The missile's inertial autopilot system contains a 3-axis fiber-optic gyroscope (FOG) and 3-axis accelerometer which stabilizes the missile in fight. The control logic of the laser beam-riding guidance system is designed to cause the missile to overfly the target vehicle by a height of approximately 0.75 meters at which point a combined laser and magnetic fuze triggers the missile's downward firing warhead. The EFP warhead weighs 2.3 kg and employs a dual tantalum liner and contains 1.05 kg of polymer bonded HMX explosive and can penetrate in excess of 130 mm of RHA, sufficient to penetrate the thinner top armor of most targets.

The rear part of the missile contains the propulsion section with two-stage soft launch system. The missile employs two motors in tandem separated by a burst disk with a common nozzle; a low-thrust launch motor which ejects the missile from the launch tube at a velocity of 25 m/s and a higher thrust flight motor which activates approximately 5 meters after the missile has cleared the launch tube and accelerates the missile to a maximum velocity of 300 m/s. The launch motor allows the missile to be launched from buildings or other enclosures without the risk of back-blast injury to the user. Both motors employ minimum smoke cross-linked doublebase (XLDB) propellant to minimize the launch signature of the missile. Stabilization is provided by four spring loaded fins located at the rear of the missile around the rocket motor case which spring out after the missile has cleared the launch tube to stabilize the missile in flight.

Launch Tube Assembly (LTA):
The missile launch tube assembly (LTA) consists of a straight cylindrical tube constructed from transversely wound fiberglass/epoxy with large foam rubber shock absorbers mounted at each end of the fiberglass launch tube and an L shaped foam rubber shoulder pad located on the underside in the middle of the launch tube. A locking hinge mounted to the launch tube is used to attach and detach the CLU.

by **The Technocratic Syndicalists** » Wed Aug 02, 2017 10:02 pm

RBS 93 Onyx

General Characteristics:
Type:
Air-to-surface guided missile

Launch platform:
Rotary wing and fixed wing aircraft

Guidance:
Tri mode millimeter wave (MMW), imaging infrared (IIR), and semi-active laser (SAL) seeker
Physical Characteristics:
Weight:
54 kg

Length:
1.8 m

Diameter:
0.18 m

Warhead:
9 kg multi-purpose shaped charge
Performance Characteristics:
Propulsion:
Solid fuel rocket

Speed:
550 m/s

Range:
25 km (rotary wing), 40 km (fixed wing)

Overview:
The RBS 93 Onyx is an air-to-surface, fire-and-forget, anti-armor missile which can be launched from both rotary wing and fixed wing aircraft. The missile features a unique tri-mode seeker combining a millimeter wave (MMW) active radar, passive imaging infrared (IIR) detector, and semi-active laser (SAL) sensor into a common aperture effective at detecting and tracking moving and stationary targets in all weather conditions and a multi-purpose tandem shaped charge warhead effective against armored vehicles, buildings and bunkers, and small warships.

Airframe & Propulsion:
The missile features a cylindrical S2 glass/epoxy filament-wound composite fuselage divided into five sections; seeker section containing the missile's tri-mode seeker, counter-active protection system jammer, and impact fuze, warhead section with tandem chaped-charge warhead and electro-mechanical safe & arm device (ESAD), guidance electronics section which contains the missile's inertial measurement unit (IMU), guidance computer, thermal battery, and software defined radio with 2-way RF datalink antenna, and propulsion & control section which contains the missile's solid fuel rocket motor and electro-mechanical control actuators for the missile's tail control fins. The missile also features a set of mid-body mounted fiberglass strakes to provide additional lift during flight. The missile's rocket motor employs a minimum smoke elastomer-modified cast double-base (EMCDB) propellant containing nitroglycerin (NG), plasticized pentaerythritol−polycaprolactone prepolymer (PE−PCP), HMX, and ammonium perchlorate (AP) which is ignited at launch using a 974 nm near-infrared diode laser and propels the missile off its launch rails to a burnout velocity of around 550 m/s.

Guidance:
The RBS 93 missile features a tri-mode seeker combining a millimeter wave (MMW) active radar, passive imaging infrared (IIR) detector, and semi-active laser (SAL) sensor into a common aperture. The millimeter wave radar seeker is a W band (94 GHz) frequency-modulated continuous-wave (FMCW) seeker which is effective against land and sea targets in all weather conditions and in the presence of battlefield obscurants. The radar seeker employs a combination of high-resolution range profile (HRRP) and doppler beam sharpening (DBS) enhanced high-resolution burst-SAR mode to image both moving and stationary targets detected by the seeker for automous target recognition purposes. The imaging infrared (IIR) seeker is a 640 x 480 pixel uncooled detector which operates in the long-wave infrared spectrum (8 to 12 µm) and provides passive day and night detection of moving and stationary vehicle targets. The semi-active laser (SAL) sensor is co-located with the infrared detector aperture and allows either the launch platform or a forward observer to designate targets with a 1.06 µm laser designator which the missile can then attack. The tri-mode seeker enables the missile to be used in either direct attack/lock-on-before-launch (LOBL) mode or in various indirect attack modes with lock-on-after-launch (LOAL) capability. In direct attack/lock-on-before-launch (LOBL) mode the missile attacks targets which are first detected and tracked by targeting sensors on the launch platform. Targeting information from the launch platforms sensor is handed off to the missile which then locks on to the target with its own seeker while still on the launch rail before the missile is launched at the target. The high off-boresight (HOBS) capability of the seeker allows targets up to 90 degrees off the aircraft's flight path axis to be locked onto and attacked in direct-fire mode. In indirect modes the missile is launched at targets not directly visible to the launch aircraft where the missile is then programmed to search for targets autonomously with its seeker. The missile first guides itself to the predicted target location using it's IMU where upon reaching the target area the MMW seeker is activated first and performs a scan of the target area and prioritizes targets based on their location and velocity. The IIR seeker will be then be activated and both MMW and IIR seekers will perform automatic target recognition (ATA) in tandem to determine which targets in the target area should be attacked. When a target has been selected the The IIR seeker is used for terminal tracking and aimpoint selection with MMW used as a backup should the target become obscured. Three indirect fire modes are supported by the weapon; point attack, column attack, and area attack

Point Attack: In point attack mode a single missile is programmed to search a given target area defined by the launch aircraft for a specific target. After launch the missile performs a flyout to the designed target area where the missile then climbs or descends to a programmed search altitude and activates its seeker which sweeps back and forth across the ground track corresponding to the ground search area defined before launch. When the desired target is acquired the missile is programmed to perform a terminal dive down onto the target, striking its more vulnerable top armor. If the seeker does not detect the target in the defined search area the missile is programmed to fly to a designated self destruct point outside of the target search area before self destructing.

Column Attack: In column attack 3 to 12 missiles are fired at a column of tanks or other vehicles with each missile fired attacking the nth target. The mode is similar to point attack mode is except the missile search area is programmed to correspond to the approximate length and width of a vehicle column which has been detected by an airborne or space based radar sensor. The first missile which enters the search area is programmed to attack either the first or last vehicle it detects, the second missile then attacking the second or second-to-last target, etc, until all vehicles in the column have been attacked and destroyed. The automatic-target-resolution capability of the seeker allows for soft-skinned vehicles in the column of tanks to be ignored is so desired.

Area Attack: In area attack mode 3 to 12 missiles are programmed to search and attack a programmed target area containing multiple target vehicles. This mode is also similar to point attack mode but uses a much larger search area corresponding to a dispersed battlefield target such as a tank company or surface-to-air missile site. In area attack mode each missile will be programmed to search an area within the larger target area, attacking the nth target it detects until all targets within the search area have been engaged.

For defeating targets equipped with active protection systems the seeker section of the missile also contains a counter-active protection system jammer designed to disable the APS fire control radar so that the targeted vehicle remains vulnerable to the missile. The system employs a series of conformal end-fire antennas located around the nose of the missile including two receiving antennas and two transmitting antennas. The receiving antennas are used to detect emissions from target APS radars where once detected a jamming signal is generated by a jammer techniques generator built into the missile's guidance computer and then amplified using an in-transmitter amplifier and subsequently radiated toward the target APS radar using the transmitter antennas to disable the enemy radar and prevent it from accurately tracking the round and initiating an intercept before the round can strike the target vehicle. The transmitter antennas operate across the 10- 40 GHz frequency range and employ the electronically conductive front end of the missile as an antenna, generating a jamming waveform which is emitted in a +/- 10° cone in the direction of target. The jammer is activated in the last 50 to 75 meters of flight where the round uses IIR for terminal guidance in order to avoid jammer emissions interfering with the round's own MMW radar seeker.

Warhead & Fuzing:
The missile is equipped with a 9.0 kilogram multi-mode tandem shaped-charge (HEAT) warhead combing blast-fragmentation and shaped-charge effects which is effective against both armored and unarmored targets. The main warhead consists of an HF-1 high-fragmenting steel case containing 5.7 kilograms of polymer-bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB), variable thickness molybnedum elliptical shaped charge liner, PEGAB (PolyEster with GlAssBubbles) wave-shaper, central and peripheral detonators, and aluminum electro-mechanical safe & arm device (ESAD) housing. A precursor warhead employing a two-layered molybdenum shaped charge liner and containing 1.0 kilograms of HMX based polymer-bonded explosive, is located ahead of the main warhead in the seeker section of the missile and serves to defeat any explosive reactive armor (ERA) tiles on the target before the main warhead detonates. When used against armored vehicles the warhead is detonated using the peripheral detonators which creates a high speed, small diameter penetrating jet capable of penetrating more than 1,500 mm RHA after ERA. For attacking buildings, fortifications, unarmored vehicles, or other soft targets the main warhead is initiated with the central and peripheral detonators which cause the warhead's copper shaped charge liner and high-fragmentation steel case to break up and release over 9,000 high-velocity fragments, creating a lethal-zone to exposed personnel over 40 meters in diameter

by **The Technocratic Syndicalists** » Sat Aug 05, 2017 12:11 am

Rb 85

General Characteristics:
Type:
Short range surface-to-air missile

Launch platform:
Vehicle

Guidance:
laser beam-riding
Physical Characteristics:
Weight:
85 kg

Length:
2.4 m

Diameter:
0.16 m

Warhead:
12.5 kg directional blast-fragmentation
Performance Characteristics:
Propulsion:
Solid-fuel rocket

Speed:
Mach 5.5 (1.9 km/s) burnout

Maneuverability:
70 G

Operational range:
16 km

Flight altitude:
8 km

Overview:
The Rb 85 is a short range hypervelocity surface-to-air missile used by SDI's FlKpfw 502 Orca self propelled air defense system.

Airframe & Propulsion:
The RBS 85 is missile is powered by a solid-fuel rocket motor employing GAP/HMX/ADN (25.5% Glycidyl Azide Polymer, 4.5% Plasticizer, 58.5% Ammonium Dinitramide, and 11.5% HMX) insensitive high-energy smokeless propellant. The GAP/HMX/ADN propellant has a higher burning rate and specific impulse than traditional Al/AP/HTPB composite or double base propellant and is completely smokeless, enabling easier tracking of the missile by the launch vehicle's targeting sensors and proving less visual approach warning to the target. The motor employs a boost-sustain propellant grain with a 7:1 thrust ratio which provides a peak thrust of 170 kN and accelerates the missile at over 450 g to a velocity of mach 5.5 in just under 1.5 seconds. The motor case is constructed from transverse wound carbon-fiber-reinforced polyetheretherketone (CFR-PEEK) with an internal aramid-filled ethylene propylene diene monomer (EPDM) insulation and and an external sacrificial kevlar fiber/phenolic composite overwrap to protect the motor case from the extreme thermal loads experienced during hypersonic flight. The lightweight nozzle features a titanium and carbon fiber reinforced PEEK load bearing structure with silica phenolic reinforced resin insulation. The missile steers using a combination of four pneumatically actuated tail fins constructed from C/Sic ceramic matrix composite and a jet-vane thrust-vector control (TVC) system which gives the missile up to 70 g overload at ranges up to 12 kilometers.

Guidance:
After launch the missile and target are tracked by the vehicle's infra-red and electro-optical tracking sensors and steering instructions are sent to the missile using a 10.6 μm CO2 laser which transmits encoded pulses to a set of rear-facing laser detectors on the missile's fins. The CO2 guidance laser is part of the laser beam-riding guidance system and produces an overlapping group of conical laser beams which are detected by a group of four laser receiver son the tail fins of the missile which is then used by the missile's autopilot to steers the missile towards the aimpoint where the laser designator beams intersect. The CO2 laser illuminator includes a variable focal length lens which decreases the diameter of the laser beam as the missile approaches the target to minimize the probable miss distance at the target.

Warhead
The missile contains a 12.5 kilogram directional blast-fragmentation warhead which is detonated either by an electro-optical proximity fuze (for air targets) or an impact fuze (for ground targets or ultra low altitude air targets). The warhead consists of an HMX explosive filled cylinder surrounded by a sleeve of pre-fragmented tungsten shrapnel. The cylinder and fragmentation sleeve surrounded by twelve radial strips of HMX explosive which can each be independently detonated. When the warhead is fuzed the charges facing the strips on the side facing the target are detonated, causes the pre-fragmented case to flatten in the direction of the target. The main charge inside the case and the line charges on the opposite side of the target direction are then detonated, causing the fragments in the flattened part of the case to be ejected in the direction of the target at extremely high velocity.

by **The Technocratic Syndicalists** » Tue Aug 08, 2017 12:07 am

Rb 75

General Characteristics:
Type:
Long range surface-to-air and anti-ballistic missile

Launch platform:
Ship VLS, TEL

Guidance:
X band active radar homing (ARH/SARH), INS/GPS, 2-way RF datalink
Physical Characteristics:
Weight:
2,000 kg

Length:
6.8 m

Diameter:
0.56 m

Warhead:
90 kg blast fragmentation
Performance Characteristics:
Propulsion:
Two stage solid fuel rocket

Speed:
Mach 9.0 (2.7 km/s) burnout

Maneuverability:
60 G

Operational range:
500 km (aircraft), 900 km (land target)

Flight altitude:
37 km

Overview:
The Rb 75 is a long range surface-to-air missile designed by SDI Missile Systems. The Rb 75 is intended to engage fixed and rotary-wing aircraft, unmanned aerial vehicles, and cruise missiles along with ballistic missiles in their terminal phase of flight. The Rb 75 can also be used as a high speed anti-ship missile and against land targets as a tactical ballistic missile.

Airframe & Propulsion:
The Rb 75 missile is a two stage missile consisting of an upper stage with a radome, guidance and navigation section, warhead section, upper stage propulsion section, and control actuator section which is attached to a first stage booster section. Both missile stages employ solid fuel rocket motors with the first stage employing a 1.7 meter long motor and the second stage employing a 2.9 meter long motor. The first stage motor weighs 710 kg with 470 kg of propellant and burns for six seconds with a peak thrust of 175 kN while the second stage motor weighs 1,000 kg with 820 kg of propellant and burns for 20 seconds with a peak thrust of 130 kN. Both motor stages accelerate the missile to a burnout speed of around mach 9 (2.7 km/s). Both first and second stage motors feature graphite/epoxy wound motor cases with internal aramid-filled ethylene propylene diene monomer (EPDM) insulation and employ a high energy solid propellant with a 90% solid loading consisting of 20% aluminum, 24% HMX, 46% AP, and 10% HTPB. The throat and nozzle of each m5 otor is constructed from triaxially braided 3-D carbon-carbon composite and both stages feature gimballed thrust-vector control using an electro-mechanically actuated ball nozzle joint providing +/- 14.5°thrust vectoring on the first stage and +/- 12.0° thrust vectoring on the second stage. The second stage additionally features four hydraulically actuated aerodynamic control fins powered by an electrohydraulic power system in the second stage consisting of a thermal battery, motor pump, oil reservoir, gas pressure bottle, and accumulator.

Guidance:
The Rb 75 missile is guided by command-inertial guidance system with an active homing radar seeker for terminal guidance. The missile can be directly launched at short to medium range targets in fire-and-forget mode and at longer range targets using command-inertial midcourse guidance with active-radar terminal-homing. Command inertial guidance uses the X band fire control radar of the launching ship or surface-to-air missile battery to track the target in track-while-scan (TWS) mode, giving the target no indication of missiles launch. The missile is initially guided via command-inertial guidance with the launch platform's radar used to transmit guidance updates to the missile via a 2-way RF datalink with antennas located on the aft fuselage of the missile upper stage. The launch platform will then guide the missile towards the target until the missile closes within the acquisition range of the seeker where the seeker is activated and acquires the target. After successfully acquiring the target the missiles will use the 2-way RF datalink to send a command guidance termination signal back to the launch platform which then ceases command guidance, the missile then homing in on the target autonomously.

The X band active radar seeker consists of a solid state transmitter consisting of a slotted waveguide flat array antenna attached to a 2-axis electromechanically actuated and stabilized gimbal with 55° off boresight actuation capability. The seeker is controlled by an integrated guidance processor which handles seeker operation, inertial guidance inputs, missile navigation and autopilot, and adaptive fuzing. The seeker is coupled to a 6-axis inertial measurement system (IMU) consisting of three fiber-optic gyros and 3 solid-state silicon accelerometers. The IMU is coupled to a 24 channel dual-frequency (L1/L2) SAASM (Selective Availability Anti-spoofing Module) based GPS receiver to create an INS/GPS system which provides seeker stabilization in addition to accurate all-weather midcourse guidance for the missile. With the INS/GPS guidance system the Rb 75 can also be used as a ballistic missile with the ability to attack fixed, geolocated land targets at ranges up to 900 kilometers with a weather independent <3 meter CEP.

Warhead
The Rb 75 missile employs a blast-fragmentation warhead which consists of 1,000 50 gram reactive tungsten fragments surrounding a 50 kilogram polymer bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB) core. The reactive tungsten shrapnel is made from a PTFE/Aluminum/Tungsten (82.5% W, 10% PTFE, 7.5% Al) alloy which is inert under normal conditions but unlike regular shrapnel will explode and burn when subjected to the stress of hypervelocity impact with a solid object. The warhead is triggered by a dual-mode pulse-doppler proximity fuze system consisting of a pair of slotted waveguide transmit/receive antennas flush with the missile skin located on either side of the warhead. The fuze is designed to operate in two modes which are programmed before launch; a mode with a warhead initiation delay which is used when engaging air breathing targets and a mode with zero delay which is used for engaging ballistic missiles. In addition to the proximity fuzes the missile also has an impact fuze consisting of piezoelectric MEMS accelerometer which senses missile impact with a target.

by **The Technocratic Syndicalists** » Wed Sep 13, 2017 8:55 pm

RBS 89 Excalibur

General Characteristics:
Type:
Hypersonic boost-glide missile

Launch platform:
Aircraft

Guidance:
SAR (Synthetic Aperture Radar) plus INS/GPS
Physical Characteristics:
Weight:
2,500 kg

Length:
7.0 m

Diameter:
0.70 m

Warhead:
125 kg blast fragmentation
Performance Characteristics:
Propulsion:
2-stage solid-fuel rocket

Speed:
Mach 15 (4.5 km/s) burnout

Range:
4,500 km

Overview:
The RBS 89 Excalibur is an air-launched launched hypersonic boost-glide missile intended to attack heavily defended time-sensitive targets. The missile is essentially a smaller version of SDI's RBS 97 missile designed to be launched from bomber aircraft as opposed to missile submarines. The missile employs a maneuvering boost-glide re-entry vehicle with large cross-range capability and flies a non-ballistic depressed trajectory to minimize detection range by hostile air defense and early-warning radar systems.

Airframe & Propulsion:
The Excalibur is a two-stage solid-fuel missile employing high-performance composite modified double base propellant. Both first and second stage motors feature graphite/epoxy wound motor cases and use NEPE-75 composite modified double base (CMDB) propellant consisting of 25% polyethylene glycol (PEG), nitrocellulose (NC), nitroglycerine (NO), and hexadiisocryanate (HDI) binder and 75% energetic solids including aluminum fuel and both ammonium perchlorate (AP) and HMX oxidizer. The throat and nozzle of each motor is constructed from 3-D carbon-carbon composite. The first stage employs a nozzle with a 7:1 expansion ratio with a first stage vacuum isp of 260 seconds while the second stage employs a 30:1 expansion ratio nozzle with a second stage vacuum isp of 280 seconds. Burn time for both stages is around 30 seconds. The second stage also features a thrust-vector control system using an electro-mechanically actuated ball nozzle joint. First stage control is provided by four movable tail fins which provide aerodynamic control during first stage burn. Both motor stages accelerate the missile to a burnout velocity of mach 15 (~4.5 km/s) at an altitude of around 40,000 meters and a downrange distance of around 500 kilometers where the nosecone is ejected and the missile's hypersonic glide vehicle (HGV) separates from the second stage and begins its hypersonic glide towards the target. The missile employs a lifting-body hypersonic glide vehicle (HGV) constructed from Ti-6Al-4V titanium alloy with an aeroshell constructed from hafnium carbide (FfC) coated 3-D carbon/carbon phenolic which is bonded to the underlying titanium structure through pyrolytic graphite supports. Steering of the glide vehicle is accomplished using four electro-mechanically actuated C/SiC ceramic matrix composite body flaps blended into the rear of the vehicle which provide pitch, roll, and yaw control during flight.

Guidance:
The missile is guided in flight through a combination GPS/INS system which combines a radiation hardened strategic-grade inertial measurement unit employing 3-axis laser-ring gyros (LRGs), 3-axis pendulous integrating gyroscopic accelerometer, and 3-axis magnetometer which is augmented with a SAASM (Selective Availability Anti-spoofing Module) based GPS receiver employing two dual-frequency wideband GPS antennas blended into the rear upper surface of the glide vehicle. The INS system is used during the initial phase of flight when the vehicle is subjected to plasma blackout conditions, transitioning to hybrid GPS/INS navigation when the plasma cloud around the vehicle has dissipated enough to allow GPS signal transmission. Terminal guidance is provided a synthetic aperture radar (SAR) integrated into the underside of the reentry vehicle. The radar employs a microstrip patch array antenna operating in the X band (9.3 GHz center frequency) which is blended into the underside of the vehicle behind the nose and covered by a projectile carbon/carbon cover which is ejected during the terminal homing phase of flight. The radar has a maximum slant range of around 35 kilometers and operates in strip-map mode with a maximum swath width of around 8,000 meters and provides <1 meter cross range resolution at a vehicle altitude of 30,000 meters. The SAR provides GPS independent terminal navigation and is used to acquire relocating vehicle targets using an automatic target recognition (ATR) alogirhtm which employs doppler beam sharpening (DBS) imaging techniques to identify ballistic missile launchers, air defense radars, and other high-value targets.

After the reentry vehicle is released from the second stage of the missile at a velocity of 4.5 kilometers per second at an altitude of approximately 40,000 meters the vehicle orients itself using it's INS in order to establish an optimal angle of attack before beginning its hypersonic glide towards the intended target area. After gliding to the intended target area at hypersonic speeds the glide vehicle performs a series of S-shaped roll-reversal maneuvers while using its synethic aperture radar to scan across the surface for its intended target. After detecting its target the glide vehicle performs a high-G pull-down maneuver from a final glide altitude of around 30,000 meters and dives down sharply towards the intended target, impacting at a velocity of around 1,000 m/s.

Warhead & Fuzing:
The hypersonic glide vehicle (HGV) of the Excalibur contains a structurally integrated 125 kilogram multipurpose blast-fragmentation warhead which is effective against a variety of soft targets including unreinforced structures, unarmored and lightly armored vehicles, parked aircraft, ballistic missiles, and air defense systems. The warhead consists of an outer fragmentation sleeve with over 25,000 5 mm reactive tungsten alloy cubes embedded into a polymer matrix which surrounds a cylindrical polymer bonded HMX explosive charge (92% HNIW, 4.8% BDNPA/F, 3.2% CAB). When the warhead is fuzed the explosive charge detonates and the reactive tungsten fragments are released in a circular pattern around the glide vehicle at extremely high velocity. The reactive shrapnel is made from a PTFE/Aluminum/Tungsten (82.5% W, 10% PTFE, 7.5% Al) alloy which is inert under normal conditions but unlike regular shrapnel will explode and burn when subjected to the stress of hypervelocity impact with a solid object.

by **The Technocratic Syndicalists** » Sun Aug 16, 2020 9:46 am

RBS 92 Shrike

General Characteristics:
Type:
Air launched ballistic missile

Launch platform:
Aircraft

Guidance:
stellar-inertial/GPS, passive RF, terminal millimeter wave active RF
Physical Characteristics:
Weight:
800 kg

Length:
4.0 m, 4.5 m with tail fairing

Diameter:
0.38 m

Warhead:
100 kg reactive fragment blast fragmentation
Performance Characteristics:
Propulsion:
Solid fuel rocket

Speed:
2.0 km/s (mach 6) burnout

Range:
500 km

Overview:
The RBS 92 Shrike is an air-launched ballistic missile designed by SDI Missiles & Fire Control. The RBS 92 is a combination long range strike and anti-radiation missile intended to strike mobile and relocatable targets including integrated air defense radars, missile transporter erector launchers, and electronic warfare systems in anti-access/area denial environments.

Airframe & Propulsion:
The RBS 92 consists of a circular composite fuselage divided into four sections, a guidance and control section which contains the missile's combined active and passive radar seeker and astro-inertial/GPS system, a warhead section which contains the missile's reactive fragment blast fragmentation warhead and electronic safe and arm device (ESAD), propulsion section which contains the missile's solid fuel rocket motor, and control actuation system which contains the rocket motor nozzle and the missiles' four tail control fins and electro-mechanical servo actuators. The missile's rocket motor is 2.5 meters long and is constructed from transverse wound carbon-fiber-reinforced polyetheretherketone (CFR-PEEK) with an internal aramid-filled ethylene propylene diene monomer (EPDM) insulation layer and an external layer of S-10 silicone reinforced phenolic ablator. The rocket motor contains 450 kilograms of SDI's 75% HNIW, 25% GAP high performance low observable propellant which is ignited using an Nd:YAG laser igniter system. The motor provides a peak thrust of over 9.0 kilonewtons and burns for 10 seconds, accelerating the missile to a peak burnout velocity in excess of 2.0 km/s. The nozzle is made from 3D carbon-carbon composite with a titanium nozzle shell and aft enclosure which also serves to mount the missile's four aerodynamic control fins and high torque electro-mechanical actuators. The missile's four tail control fins are constructed from carbon fiber reinforced polyimide with two composite chines on the sides of the fuselage also contracted from carbon fiber reinforced polyimide which act as wiring tunnels and reduce the missiles radar cross section. For external carriage a composite carbon fiber reinforced bismaleimide (BMI) tailcone is fitted to the aft of the missile which is jettisoned by the exhaust of the rocket motor upon ignition.

Guidance & Navigation:
[tab=25]The RBS 92 combines a hybrid stellar-inertial/GPS system midcourse guidance system with a terminal seeker combined broadband passive radar homing system with an active millimeter wave seeker. The midcourse guidance unit contains a miniature optical wide-angle-lens startracker (OWLS) unit with a holographic optical lens blended into the upper surface of the missile forebody containing a megapixel (1,000 vs 1,000 px) CCD imager operating in the far red band (0.6-0.8 μm). The system simultaneously images three separate 4° field of view (FOV) with a total 48° by 48° field of regard, providing highly accurate stellar fixes in flight using a 61 star catalog stored in the guidance system computer with a <30 meter GPS independent position fix accuracy capability. The startracker is coupled to an SDI designed TNS 450 tactical-grade timing and inertial measurement Unit (TIMU) which combines three milli-Hemispherical Resonator Gyroscope (mHRG) and three quartz resonating beam accelerometers (RBA) in a low SWaP package (500 cc volume, <1.0 kg mass, <5 watts max power consumption) package which provides <0.0003°/√hr gyro angle random walk and < 0.0001 °/hr bias stability performance. GPS capability is provided by an SDI designed GPS spatial temporal anti-jam receiver (GSTAR) unit with wide area differential GPS (WADGPS) capability providing <1 meter resolution 3-dimensional position accuracy in flight. A 2-way RF datalink operating in the L band connected to a software defined radio (SDR) is also fitted to the missile which allows guidance updates from the launch aircraft to be sent to the missile and flight and for weapon impact assessment (WIA) information including real time missile status, location and target information to be sent back to the launch aircraft in flight.

The passive seeker assembly consists of of a total of 12 conformal, ultra-wideband (XWB) antennas placed radially around the missiles forward fuselage behind the seeker assembly which provide 360 degree detection of radar signals in the 500 MHz to 40 GHz range (UHF - Ka Band). The 12 antennas feed into a photonic receiver unit with >40 GHz of instantaneous bandwidth and provides accurate detection, classification, and angle of arrival (AoA) information of incident radar waves and allows the missile to passively home in on emitting ground based radars and electronic warfare systems. The active radar seeker consists of a strapdown W band (94 GHz) active solid state electronically scanned array radar system which is housed ahead of the passive radar antenna assembly in the missile's reaction sintered silicon nitride radome in the nose of the missile. The radar antenna is 17 centimeters in diameter and contains over 1,000 94 GHz SiO2/Si3N4 dieletric membrane based MEMS (Micro Electro Mechanical System) T/R modules with integral MEMS phase shifters and power amplifiers. The radar is capable of scanning +/- 60° off boresight in both azimuth and elevation. The millimeter-wave provides an extremely high angular resolution for target tracking and discrimination and features over 1 GHz of instantaneous bandwidth for increased ECM resistance. ECCM features of the seeker include frequency-modulated continuous-wave (FMCW) operation to minimize probability of detection by enemy receivers, high instanenous bandwidth, dual-polarized aperture, randomized burst transmissions, active sidelobe cancellation, and home-on-jam (HOJ) functionality.

Warhead & Fuzing:
The RBS 92 contains a 100 kilogram reactive fragment blast fragmentation warhead effective against structures, unarmored and lightly armored vehicles, surface vessels. The warhead consists of an outer titanium casing containing a fragmentation sleeve with over 30,000 reactive aluminum-PTFE fragments embedded in a polymer matrix which surrounds a 25 kilogram cylindrical polymer-bonded explosive (92% HNIW, 4.8% BDNPA/F, 3.2% CAB) charge. When the warhead is fuzed the explosive charge detonates and the reactiven fragments and shrapnel from the titanium casing are released in a circular pattern around the missile at extremely high velocity. The reactive shrapnel is made from a 75% PTFE/ 25% aluminum mixture which is inert under normal conditions but unlike regular shrapnel will explode and burn when subjected to the stress of hypervelocity impact with a solid object. The outer titanium casing provides structural support for the warhead in flight as well as additional reactive capability when the warhead is detonated.

by **The Technocratic Syndicalists** » Mon Aug 17, 2020 8:25 am

RBS 110 Scimitar

General Characteristics:
Type:
Land attack and anti-ship missile

Launch platform:
Aircraft

Guidance:
Tri-mode Active RF/Passive RF/Imaging infrared (IIR), INS/GPS, 2-way RF datalink
Physical Characteristics:
Weight:
1,000 kg

Length:
5.0 m

Diameter:
0.50 m

Warhead:
250 kg reactive blast-fragmentation
Performance Characteristics:
Propulsion:
Liquid-fuel integral rocket-ramjet

Speed:
Mach 5.5 (high altitude), mach 3.0 (sea level)

Range:
1,000 km (hi-hi-hi), 200 km (lo-lo-lo)

Overview:
The RBS 110 is an air launched supersonic/hypersonic anti-ship and land attack cruise missile designed by SDI Missile Systems. The RBS 110 features a liquid fuel integral rocket ramjet propulsion system enabling high supersonic cruise speeds at low altitudes and hypersonic cruise at high altitudes and uses a tri-mode seeker with active RF, passive RF, and imaging infrared capability for maximal ECCM resistance and terminal seeker performance against targets in high clutter encironments.

Airframe & Propulsion:
The RBS 110 features a rectangular lifting-body fuselage divided into five sections: seeker & guidance electronics section containing the missile's tri-mode seeker, INS/GPS navigation system, and guidance electronics, warhead section containing 250 kg warhead and electronic safe and arm device (ESAD), fuel section containing the missile's liquid hydrocarbon fuel, propulsion section containing the missile's ramjet combustor and integral solid rocket booster, and tail assembly containing the ramjet nozzle and the missile's tail control-actuation system. The missile features a low-RCS lifitng body with a rectangular cross section which is constructed from Ti-6Al-4V titanium alloy covered with an ablative silica phenolic TPS with the radome constructed from reaction-sintered silicon nitride (Si3N4). The missile employs a bank-to-turn maneuvering scheme and is controlled by four hydraulically actuated tailfins constructed from Inconel 718 which are arranged in an X configuration at the rear of the missile.

The RBS 110 missile employs an integral rocket-ramjet propulsion system which combines a solid fuel rocket booster with a liquid-fuel thermally throated ramjet (TTRJ) sustainer engine. The integral nozeless solid rocket motor is packed inside the ramjet combustor and contains 205 kg of high energy density solid propellant (20% aluminum, 24% HMX, 46% AP, and 10% HTPB binder) and ignites after launch to boost the missile to a ramjet takeover speed of mach 3.0 at an altitude of 20,000 meters. After solid motor burnout the thermally throated ramjet rmotor is ignited and accelerates the missile to a cruise velocity of mach 5.0 at an altitude of 25,000 meters. The ramjet is fed from a rearward swept, mixed-compression chin inlet constructed from Inconel 718 alloy which is mounted underneath the radome structure and feeds the ramjet combustor through an S-shaped duct in the missile's centerbody. The fuel tank for the ramjet is wrapped around the central S-duct and contains 215 kg of synthetic RJ-6 fuel which is fed into the ramjet combustor using a turbopump propellant feed system. The ramjet combustor is constructed from 3-D carbon-carbon composite while the ramjet nozzle is constructed from tape wrapped silica phenolic. The ramjet combustor is designed for a 1950°C operating temperature and provides for a nominal specific impulse of 1,300 seconds at cruise conditions.

Guidance & Navigation:
The RBS 110 employs a tri-mode seeker system which combines a Ku band (14 GHz) active radar seeker, 0.5-20 GHz passive radar seeker, and a cooled imaging infrared (IIR) seeker. The Ku band (14 GHz) radar seeker is mounted in the faceted nose radome and is optimized for all-weather detection and engagement of surface ship targets. The seeker employs an active phased array antenna using gallium nitride (GaN) T/R modules and is scanned electronically in elevation and mechanically in azimuth with a +/- 90° azimuth and +/- 60°elevation scan capability. The seeker generates and transmits randomized low-power noise signals to detect targets, a copy each generated randomized noise signal being stored in the seeker's active memory as to allow correlation with incoming signal returns. The high bandwidth of the seeker (>1 GHz) combined with randomized noise signals results in extremely high range resolution and allows for both simultaneous measurement of range and doppler shift of the target. Extremely high range and doppler resolution of the seeker support clutter discrimination in littoral environments as well as automatic target recognition (ATR) and aimpoint selection capability. Additional ECCM features of the seeker include low-power, narrow beam-width transmissions, dual polarized antenna to counter angle deception jamming, and high frequency agility. The passive radar seeker is mounted behind the Ku band radar seeker in the missile's nose radome and consists of a dual mode planar spiral high band antenna and eight element low band antenna array providing 0.5-20 GHz emission detection, identification, and direction finding capability which covers typical surface ship air search, navigation, and fire control radar bands. The passive radar seeker alloys the missile to approach emitting targets radar silent, only using the active radar seeker for terminal homing and target aim-point selection. The imaging infrared seeker is mounted above the radar seeker in a separate fairing above the nose and is covered by an inconel shroud which is ejected during the terminal homing phase.

The seeker assembly is coupled with a midcourse guidance unit (MGU) which contains a 2-way satellite communications datalink and a GPS/INS autopilot system combining a 6-axis strapdown inertial measurement unit with three laser-ring gyroscopes (LRG) and three quartz resonating beam accelerometers (RBA) with a Selective Availability Anti-Spoof Module (SAASM) based GPS receiver. The autopilot unit provides for highly accurate 3D waypoint based terminal navigation and allows for engagement of stationary land targets using GPS grid-coordinates which can be uploaded to the missile before or after launch. Wide-area differential GPS (WADGPS) capability is supported by the autopilot's GPS system and enables impact CEPs of <3 meters when attacking geolocated land targets. Use of the two-way satellite communications datalink allows updated targeting data of moving ship targets to be sent to the missile and allows the missile to be vectored to other pre-programmed targets in flight or to be re-redirected to any other GPS grid coordinates within the missile's range. Missile health and status updated can also be transmitted back to the launch platform using the satellite datalink.

During a typical anti-ship engagement the target range and bearing information of the intended target, which can be provided either by the launch platform's sensors or by a third party, is down-linked to the missile's autopilot system. The missile is then launched, accelerates to a hypersonic cruise speed of mach 5.0 at an altitude of approximately 25,000 meters ASL and then uses its autopilot to follow a series of pre-programmed 3D waypoints to guide itself to the target area. At a pre-set range from the target determined by the launch mode the missile descends to around 500-600 meters ASL and activates its radar seeker and enters into a serpentine flight where the missile uses its passive radar seeker to scan for target emissions and its active radar to search back and forth across the horizon. The seeker's track-while-scan capability enables it to detect and track multiple contacts while prioritizing targets using the seeker's automatic target recognition algorithms. Once a target has been selected the activates its radar altimeter and descends to sea level where it follows a sea-skimming trajectory at 5-10 meters ASL towards the target bearing. The missile can then perform additional short pop-up maneuvers to obtain better range and bearing fixes on the target and can change its trajectory to strike the target from a different direction. When approaching the target the missile performs either a terminal pop-up maneuver or follows a terminal sea-skimming trajectory ASL while optionally performing a series of 10+ g terminal bunt and weave maneuvers, uses its radar seeker to select an aimpoint on the target ship, and then impacts the top or side of the target ship where it punches through the ship's hull before exploding inside.

Warhead:
The RBS 110 missile contains a 250 kg penetrating blast-fragmentation warhead consisting of a titanium case filled with 100 kilograms of insensitive enhanced blast polymer-bonded explosive (PBX) consisting of 65% RDX, 20% aluminum powder, and 15% HTPB binder. The warhead is fitted with a hard target smart fuze containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The detonator is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge which is armed in flight and requires a constant 500 V from the missile's power system to function.

by **The Technocratic Syndicalists** » Thu Aug 20, 2020 3:00 pm

Rb 73

General Characteristics:
Type:
Medium-range surface-to-air and anti-ballistic missile

Launch platform:
Ship, TEL

Guidance:
Ka band active RF, 2-way RF datalink
Physical Characteristics:
Weight:
350 kg interceptor, 1,050 kg with booster

Length:
4.6 m interceptor, 6.5 m with booster

Diameter:
0.25 m (intercept stage), 0.5 m (booster)

Warhead:
15 kg lethality enhancer
Performance Characteristics:
Propulsion:
Two-stage solid fuel rocket

Speed:
Mach 5.5

Maneuverability:
60 G

Operational Range:
3-250 km

Flight Altitude:
0-40 km

Overview:
The Rb 73 is a medium-range surface-to-air missile (SAM) with hit-to-kill capability designed to intercept a variety a targets including fixed-wing and rotary-wing aircraft, unmanned aerial vehicles, subsonic and supersonic anti-ship cruise missiles, and short and medium range ballistic missiles.

Airframe & Propulsion:
The Rb 73 is a two stage missile with a 50 cm diameter booster attached to a 25 cm diameter upper intercept stage. The booster motor weighs 700 kilograms and consists of a solid propellant rocket motor with a hydraulically gimballed supersonic split line (SSSL) nozzle with /- 20 ° gimbal angle. The booster is constructed from filament-wound graphite reinforced polyetheretherketone (PEEK) with an internal aramid-filled ethylene propylene diene monomer (EPDM) insulation layer and contains 400 kilograms of SDI minimum-smoke insensitive tactical propellant consisting of 25.5% GAP energetic binder, 4.5% TMETN (trimethylolethane trinitrate) plasticizer, 58.5% ADN (ammonium dinitramide) oxidizer, and 11.5% HMX (Octogen) and burns for 5 seconds, accelerating the upper stage toward the target. The upper intercept stage is contracted from filament-wound graphite reinforced polyimide and consists of five sections including a guidance electronics section containing the missile's dual Ka band (35 GHz) millimeter wave (MMW) active radar seeker and MWIR (3-5 μm) imaging infrared seeker along with the missile's guidance electronics, an attitude control section (ACS) containing solid propellant attitude control motors, warhead section containing electronic safe and arm device (ESAD) and lethality enhancer warhead, rocket motor section containing the missile's dual-pulse solid-fuel rocket motor, and rear control actuation section with contains the solid motor nozzle, control-actuation system (CAS) with four moveable tailfins, and dual X and S band antennas for the missile's target data uplink (TDU) system.

The 25 centimeter diameter dual-pulse rocket motor of the upper intercept stage employs two radially-burning propellant grains with a 75/25 impulse split separated by a pair of burst disks which can each be ignited in succession at pre-programmed intervals during flight. The first pulse is designed to accelerate the missile to cruise velocity while the second pulse provides greater divert capability and additional terminal acceleration and endgame thrust vector control capability. like the booster the intercept motor employs an SDI minimum-smoke insensitive tactical propellant grain formulation consisting of 25.5% GAP energetic binder, 4.5% TMETN (trimethylolethane trinitrate) plasticizer, 58.5% ADN (ammonium dinitramide) oxidizer, and 11.5% HMX (Octogen) which combines high specific impulse and burn rate with low impact and thermal sensitivity and low exhaust signature. The motor grains are separated by elastomeric burst disk which provides thermal isolation between the adjacent propellant grains. The motor weighs 200 kilograms including 150 kilograms of solid propellant and is constructed from graphite/polyimide composite with a 4-D carbon-carbon nozzle supported by a titanium nozzle shell and aft enclosure which also serves to mount the missile's aerodynamic steering fins and associated electro-mechanical actuators.

Aerodynamic control of the missile is provided by four rear mounted tail fins actuated by compact electromechanical servomotors located in the missile's control-actuation system (CAS) at the tail end of the missile which provide pitch, roll, and yaw control during the initial flyout and cruise phase and roll control during the terminal phase. Tail control is supplemented by a the missile's attitude control system (ACS) which consists of a radial array of 180 solid propellant attitude control motors (ACMs) that thrust perpendicular to the centerline of the missile to provide pitch and yaw control during the terminal phase. The ACMs are arranged in 10 rows of 18 motors spaced evenly around the centerline which are commanded by a central motor fire circuit (MFC) connected to the missile's guidance computer. Each individual ACM consists of a graphite/polyimide motor housing with a titanium-zirconium-molybdenum (TZM) nozzle insert and contains 25 grams of 80/20 AP/HTPB solid propellant providing a total impulse of 50 N-s and peak thrust of 6.0 kN per ACM.

Guidance:
The Rb 73 features a dual radar and infrared seeker system which combines a Ka band (35 GHz) millimeter wave (MMW) active radar seeker and a mid-wave (3-5 μm) imaging infrared seeker. The Ka band (35 GHz) millimeter wave (MMW) active radar seeker is designed to provide accurate range and angle tracking of small, low signature targets moving at high and low speeds and consists of a hollow disk shaped solid state transmitter with a traveling-wave tube power amplifier mounted to a electromechanically actuated 2-axis stabilized gimbal capable of pointing +/- 60 °s off boresight in both azimuth and elevation. The millimeter-wave Ka band seeker provides an extremely high angular resolution for target tracking and discrimination and features over 1 GHz of instantaneous bandwidth for increased ECM resistance. The imaging infrared seeker consists of a 512 x 512 pixel dual-band HgCdTe (mercury cadmium telluride) starring focal plane Array (FPA) imaging infrared (IIR) seeker operating in both the the MWIR (3-5 μm) band which is cooled to 80 °K using a Stirling cycle cryocooler fed from an onboard nitrogen bottle. The infrared detector is mounted in the central hollow portion of the Ka band millimeter wave transceiver and is co-bore sighted with the radar seeker. The seeker is covered with a spherical optical dome constructed from two-layer zinc sulfide with an inner conductive grid layer which provides transmission of both millimeter wave radar and mid-wave infrared radiation. To reduce drag the spherical optical dome is covered with a von-karman ogive radome constructed from reaction-bonded silicon nitride which provides transmission of millimeter wave radar signals which is ejected prior to terminal dual mode homing. The guidance section of the missile is also equipped with a strapdown, low SWaP (size, weight, area, and power) tactical grade IMU containing 3-axis fiber-optic gyro (FOG) and 3-axis solid-state silicon accelerometers which are combined with a SAASM based GPS receiver to provide midcourse phase guidance for the missile.

Warhead
The Rb 73 is primarily a hit-to-kill missile which is designed to hit targets head on and destroy them using the kinetic energy of the collision. The hit-to-kill capability is augmented by a 15 kilogram "lethality enhancer" warhead which deploys 24 heavy metal tungsten alloy (HMTA) fragments around the centerline of the missile prior to impact in order to increase the probability the the target is hit by either the missiles or one of the fragments. The fragments are deployed at a relatively low radial velocity, decreasing the sensitivity of the fragment pattern to time fuze and radar range error. The warhead consists of a graphite/polyimide case which contains two concentric rings of 12 215 gram heavy metal tungsten alloy (HMTA) fragments surrounding a central 330 gram polymer bonded HMX (92% HMX, 4.8% BDNPA/F, 3.2% CAB) explosive charge.

by **The Technocratic Syndicalists** » Mon Aug 24, 2020 8:23 am

Rb 77 Falcon

General Characteristics:
Type:
Anti-ballistic missile

Launch platform:
Ship, TEL

Guidance:
Dual-band imaging infrared (IIR), RF datalink
Physical Characteristics:
Weight:
2,000 kg

Length:
6.5 m

Diameter:
0.60 m

Warhead:
Hit-to-kill
Performance Characteristics:
Propulsion:
Two-stage solid fuel rocket

Speed:
5.5 km/s (Mach 18) burnout

Operational Range:
1,000 km

Intercept Altitude:
20-500 km

Overview:
The Rb 77 is an anti-ballistic missile interceptor designed to provide hit-to-kill terminal phase intercept of intercontinental ballistic missile (ICBM) reentry vehicles, maneuvering reentry vehicles (MaRVs), and hypersonic glide vehicles (HGVs)

Airframe & Propulsion:
The Rb 77 interceptor consists of a two-stage solid-fuel rocket booster and an endo/exo-atmospheric kill vehicle. The two booster stages employ graphite filament wound epoxy casings with 3-D carbon-carbon nozzles and employs a high performance HNF/AL/GAP composite propellant consisting of 60% HNF (Hydrazinium nitroformate) oxidizer, 20% Aluminum fuel, and 20% GAP (Glycidyl azide polymer) energetic binder. The first stage weighs 1,300 kg including 1,000 kg of HNF/AL/GAP composite propellant and burns for six seconds, accelerating the interceptor to a first stage burnout velocity of 2.4 km/s where the second stage separates and ignites. The first stage employs an electrohydraulic actuator based gimballed nozzle with +/- 7.5° gimbal angle which is used for first-stage thrust vector control. The second stage weighs 450 kilograms including 360 kilograms of propellant and features a dual-pulse motor with two 4.5 second burns and provides additional acceleration and divert capability for the kill vehicle. The second stage features a thrust vectoring nozzle with a +/- 7.5° gimbal angle and features an integral warm-gas/cold-gas attitude control system (ACS) built into the aft end of the second stage motor which combines a cold-gas system (CGS) using compressed nitrogen thrusters and and warm-gas system (WGS) using solid-propellant gas generators and nozzles which provide roll, pitch, and yaw control while the second stage motor is firing or while the stage is coasting in between motor pulses. The interceptor's endo/exo-atmospheric kill vehicle weighs 75 kg and employs a solid-propellant divert and attitude control system (DACS) for maneuvering. The kill vehicle DACS employs a total of 10 solid propellant thrusters with variable-area pintle nozzles which allow each thruster to be throttled from 0-100% of maximum thrust for precise in-flight control. Each divert thruster includes a solid propellant rocket grain contained in a graphite/epoxy filament-wound case and a combustion chamber and nozzle constructed from 4D carbon carbon (C/C) composite with a variable throat-area pintle nozzle which allows each thruster to provide between 5 and 8,000 newtons of thrust with a maximum 200 N-s of total impulse per thruster and can provide both short and long impulse pulses to the missile to quickly and accurately position the missile to maintain seeker lock and place the missile on a collision course with the target. The 10 DACs thrusters provide roll, pitch, and yaw control during the terminal phase of intercepts and provide the kill vehicle with over 2.0 kilometers per second of divert delta-V with the ability to maneuver at up to 100 g.

Guidance:
The kill vehicle employs a dual-band imaging infrared (IIR) seeker which is used to provide endo and exo-atmopsheric target discrimination and tracking capability. The seeker uses a radiation hardened 512 x 512 pixel dual-band (MWIR and LWIR) digital-pixel focal plane array (FPA) with a 48 by 48° overall field of view mounted to a 2-axis stabilized AlBeMet alloy optical telescope assembly with selectable wide and narrow field-of view (WFOV and NFOV) modes which are selected in-flight based on whether the intercept is endo or exo-atmospheric. The optical assembly employs active line-of-sight (LOS) stabilization using the 2-axis stabilized telescope and a 6-axis laser-ring gyro IMU to provide sub-pixel image stabilization capability while the kill vehicle maneuvers at up to 100 g. Seeker acquisition range against a typical ICBM RV varies from 40 kilometers for endo-atmospheric intercepts to over 300 kilometers for exo-atmospheric intercepts. The measurements from the seeker are combined with body orientation measurements from the 6-axis laser-ring gyro IMU based altitude reference system (ARS) built into the kill vehicle which when combined with the DACS thruster system steers the kill vehicle onto the correct interception trajectory after it has detected its target. The seeker window is mounted off-axis to the kill vehicle line of sight and employs a diamond/silicon optical window actively cooled with cold nitrogen gas pumped through internal micro-cooling channels for endo-atmospheric intercepts. The cooling system is designed to allow the infrared window to survive exposure to extreme hypersonic heating and also to provide minimal flow interference so that the infrared seeker can effectively acquire its target. For exo-atmospheric intercepts the seeker window is ejected with non-explosive actuators in order to remove residual heating effects and improve seeker sensitivity. The kill vehicle and interceptor have three selectable guidance modes depending on whether launch commit and target intercept happen in the endo or exo-atmospheric phases of flight including exo-commit/endo-intercept, endo-commit/endo-intercept, and exo-commit/exo-intercept:

Exo-commit/endo-intercept: In this mode a mid-course sensor tracks the target vehicle or target cluster in its midcourse phase while it is still travelling through the exoatmosphere and queues the interceptor to launch where the interceptor then launches and intercepts the target as it enters the upper endoatmosphere. After launch the first stage burns and is discarded where depending on the intercept range the second stage is either immediately ignited (for shorter range intercepts) or the interceptor coasts before igniting the second stage (for longer ranged intercepts). After the first pulse of the second stage burns out the interceptor coasts towards the target where the second stage warm-gas/cold-gas attitude control system is used to steer the vehicle towards the desired intercept point. When the interceptor closes to within seeker range the shroud over the kill vehicle seeker is jettisoned and the kill vehicle's dual-band infrared seeker begins a wide field-of-view (WFOV) sweep of the target area. The dual-band seeker is used to discriminate the warhead from decoys in the target cluster. When the seeker has locked onto the desired target the second pulse of the second stage is ignited and the kill vehicle's solid-propellant DACS thrusters are used to steer and accelerate the kill vehicle towards the target. After second pulse burnout the kill vehicle separates from the second stage and uses its DACS thrusters to perform the final steering and corrective maneuvers before hitting the target.

Endo-commit/endo-intercept: This mode is similar to exo-commit/endo-intercept except the interceptor is launched while the target is being tracked as it re-enters the atmosphere by a terminal sensor with the target intercept happening in the lower atmosphere. In this mode there is no coast between first and second stage motor burns or between the second stage pulses with kill-vehicle shroud jettison and kill-vehicle seeker target acquisition happening during first and second stage motor burn. After second stage burn the kill vehicle separates and the kill vehicle DACS for endgame maneuvering before impact with the target.

Exo-commit/exo-intercept: In this mode target tracking, discrimination, and commit and intercept happen while the target is travelling through the exo-atmosphere in its midcourse phase. Flyout and intercept are similar to exo-commit/endo-intercept mode except the coast between first stage burnout and second stage ignition is typically much longer. In this mode target discrimination is performed by the midcourse sensor with the interceptor correlating its seeker scene in NFOV mode with that of the midcourse sensor for terminal target acquisition and homing. This mode also lets the interceptor act as an ASAT (anti-satellite) missile with the capability to intercept satellite targets in low-earth orbit.

by **The Technocratic Syndicalists** » Wed Oct 21, 2020 1:01 pm

GB 2000

General Characteristics:
Type:
Glide bomb

Launch platform:
Aircraft

Guidance:
IIR, INS/GPS, 2-way RF datalink
Physical Characteristics:
Weight:
2,600 kg

Length:
5.3 m

Diameter:
0.40 m

Warhead:
2,000 kg unitary penetrator

Performance Characteristics:
CEP:
<3 m

Range:
160 km (12,000 meter release)

Overview:
The GB 2000 is a guided glide bomb intended to destroy hardened and deeply buried targets (HDBTs). The bomb consists of a wing kit and guidance kit with electro-optic/infrared+INS/GPS guidance mated to a 2,000 kilogram bomb body which converts it into a long range precision guided munition.

Design & Airframe:
The GB 2000 weapon consists of five sections: front mounted seeker and guidance module with electro-optical/infrared seeker fuze, control module with autopilot, thermal battery, and GPS receiver, forward warhead adapter, warhead, rear warhead adapter with pivoting wing section, and tail assembly with rear tailfins and electro-mechanical control actuators.

Guidance
The GB 2000 employs an uncooled imaging-infrared focal plane array (UIIFPA) seeker contained in an injection-molded polymer housing in the nose of the weapon. The 320 x 240 pixel uncooled microbolometer array used by the seeker operates in the LWIR (7 to 13.5 µm) band and features a +/- 5° azimuth and +/- 5° elevation field of view. The imaging infrared seeker is coupled with an INS/GPS guidance system which contains a 6-axis ring laser gyro (RLG) based inertial measurement unit (IMU) and a 12 channel dual-frequency Selective Availability Anti-spoofing Module (SAASM) based GPS receiver unit which provides highly accurate all-weather midcourse and terminal phase weapon guidance.

Before launch the GPS gird coordinates of the target are determined and an image of the target taken from satellite, UAV, or reconnaissance aircraft imagery or by the launch platform's own synthetic aperture radar (SAR) or forward looking infrared (FLIR) sensors is selected and a desired aim-point on the target image specified by the pilot or WSO (Weapon Systems Officer) using a Head-Down Display (HDD) in the cockpit. The GPS grid coordinates of the target are downlinked to the weapon's autopilot and the image of the target with desired aimpoint is downlinked to the bombs seeker before the weapon is released. In addition to the specified target up to 99 other alternate target images with aimpoints and grid coordinates can be downlinked to the weapon before launch with the option to re-direct the weapon to one of the alternate targets during flight. When the aircraft comes within glide range of the intended target the weapon is released and glides toward the target area using INS/GPS midcourse guidance. During this phase the 2-way RF datalink can be used to specify one of the alternate targets, transmit imagery of a new target, or direct the bomb to strike a set of GPS grid coordinates instead. In the final 2,000 meters of flight the IIR seeker is activated and images the target area, comparing the seeker imagery with the downloaded target image to both positively identify the target and desired aimpoint. Once the infrared seeker has locked onto the target the infrared seeker to IMU alignment error is calculated to within 100 microradians and the weapon's INS/GPS guidance system is updated with the correct position, the bomb then pulling up to several Gs if necessary to align itself with the correct trajectory before impact. If the imaging infrared seeker is unable to identify or locate the target due to weather conditions or other reasons the weapon will simply follow INS/GPS guidance all the way to the target. CEP of the weapon is approximately 1 meter with the imaging infrared seeker or 3 meters when using solely INS/GPS guidance.

Warhead:
The GB 2000 employs an SDI PC 2000 hardened penetrator warhead which is designed to destroy heavily reinforced or buried structures. The bomb consists of a forged and machined 3.5 GPA (500,000 psi) tensile strength nickel-molybdenum-cobalt maraging steel (8Ni-14Mo-20Co-Fe) penetrator casing filled with 350 kilograms of enhanced blast thermobaric explosive (50% HMX, 30% Al powder, 20% PCP/TMETN energetic binder/plasticizer). The PC-2000 warhead is fitted with a base mounted hard target smart fuze (HTSF) containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The detonator is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge. With a terminal impact velocity of around mach 1 when used with a high altitude release the PC 2000 warhead is capable of penetrating over 8 meters of 34 MPa (5,000 psi) reinforced concrete before exploding.

by **The Technocratic Syndicalists** » Wed Oct 21, 2020 3:31 pm

GB 100

General Characteristics:
Type:
Miniature glide bomb

Launch platform:
Aircraft

Guidance:
IIR, INS/GPS, 2-way RF datalink
Physical Characteristics:
Weight:
125 kg

Length:
1.8 m

Diameter:
0.18 m

Warhead:
100 kg unitary penetrator

Performance Characteristics:
CEP:
<3 m

Range:
110 km (12,000 meter release)

Overview:
The GB 100 is a miniature precision guided glide bomb designed by SDI Missile Systems. The GB 100 is designed to drastically increase the loadout capability of strike aircraft and employs a high L/D sub-caliber unitary penetrator warhead with concrete penetration comparable to older generation 500 and 1,000 kilogram bombs.

Design & Airframe:
The GB 1000 weapon consists of four sections: front mounted seeker and guidance module with electro-optical/infrared seeker, warhead and wing section, control module with autopilot, thermal battery, and GPS receiver, and tail assembly with wings, rear tailfins and electro-mechanical control actuators, and RF datalink system with aft facing receiver and transmitter antenna.

Guidance
The GB 100 employs an uncooled imaging-infrared focal plane array (UIIFPA) seeker contained in an injection-molded polymer housing in the nose of the weapon. The 320 x 240 pixel uncooled microbolometer array used by the seeker operates in the LWIR (7 to 13.5 µm) band and features a +/- 5° azimuth and +/- 5° elevation field of view. The imaging infrared seeker is coupled with an INS/GPS guidance system located in the rear of the weapon which contains a 6-axis ring laser gyro (RLG) based inertial measurement unit (IMU) and a 24 channel dual-frequency (L1/L2) SAASM (Selective Availability Anti-spoofing Module) based GPS receiver which provides highly accurate all-weather midcourse and terminal phase weapon guidance enabling <3 meter CEP in all weather conditions.

Before launch the GPS gird coordinates of the target are determined and an image of the target taken from satellite, UAV, or reconnaissance aircraft imagery or by the launch platform's own synthetic aperture radar (SAR) or forward looking infrared (FLIR) sensors is selected and a desired aim-point on the target image specified by the pilot or WSO (Weapon Systems Officer) using a Head-Down Display (HDD) in the cockpit. The GPS grid coordinates of the target are downlinked to the weapon's autopilot and the image of the target with desired aimpoint is downlinked to the bombs seeker before the weapon is released. In addition to the specified target up to 99 other alternate target images with aimpoints and grid coordinates can be downlinked to the weapon before launch with the option to re-direct the weapon to one of the alternate targets during flight. When the aircraft comes within glide range of the intended target the weapon is released and glides toward the target area using INS/GPS midcourse guidance. During this phase the 2-way RF datalink can be used to specify one of the alternate targets, transmit imagery of a new target, or direct the bomb to strike a set of GPS grid coordinates instead. In the final 2,000 meters of flight the IIR seeker is activated and images the target area, comparing the seeker imagery with the downloaded target image to both positively identify the target and desired aimpoint. Once the infrared seeker has locked onto the target the infrared seeker to IMU alignment error is calculated to within 100 microradians and the weapon's INS/GPS guidance system is updated with the correct position, the bomb then pulling up to several Gs if necessary to align itself with the correct trajectory before impact. If the imaging infrared seeker is unable to identify or locate the target due to weather conditions or other reasons the weapon will simply follow INS/GPS guidance all the way to the target. CEP of the weapon is around 1 meter with the imaging infrared seeker or 3 meters when using solely INS/GPS guidance.

Warheads:
The GB 100 employs a 100 kilogram hardened penetrator warhead designed to destroy heavily reinforced or buried structures. The bomb consists of a 3.5 GPA (500,000 psi) tensile strength nickel-molybdenum-cobalt maraging steel (8Ni-14Mo-20Co-Fe) sub-caliber penetrating warhead filled with 20 kilograms of enhanced blast thermobaric explosive (50% HMX, 30% Al powder, 20% PCP/TMETN energetic binder/plasticizer). The warhead is fitted with a base mounted hard target smart fuze (HTSF) containing a precision MEMS accelerometer and micro-controller which features void sensing, layer counting, depth of penetration, and time time delay after impact fuzing modes. The detonator is entirely electronic with no moving parts and uses an exploding foil initiator (EFI) detonator to initiate the main explosive charge. With a terminal impact velocity of mach 1 when used with a high altitude release the warhead is capable of penetrating up to 1.8 meters of 34 MPa (5,000 psi) reinforced concrete before exploding.

SDI Guided Munitions Catalog [DO NOT POST]

SDI Guided Munitions Catalog [DO NOT POST]

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