SDI Guided Munitions Catalog [DO NOT POST]

by **The Technocratic Syndicalists** » Mon Oct 26, 2020 4:38 pm

RBS 86

General Characteristics:
Type:
Standoff anti-submarine missile

Launch platform:
Torpedo tube, VLS

Guidance:
INS
Physical Characteristics:
Weight:
1,800 kg

Length:
7.0 m

Diameter:
0.6 m (capsule diameter)

Warhead:
F3S Viperfish Torpedo
Performance Characteristics:
Propulsion:
Solid fuel rocket

Speed:
Mach 2.5

Launch Depth:
up to 300 m

Range:
5 - 100 km

Overview:
The RBS 86 is a long range standoff anti-submarine missile designed by SDI Missile & Fire Control Systems. The RBS 86 is available in two versions, an RBS 86S variant designed to be launched from SDI’s S70 surface ship VLS and an RBS 86U version intended to be launched from the 60 cm torpedo tubes on SDI’s Hydra and Erebus class submarines .

Airframe & Propulsion:
The RBS 86 missile consists of a single stage solid fuel rocket booster with a thrust vector control (TVC) system connected to a payload section containing an SDI F3S Viperfish lightweight anti-submarine torpedo with a ballistic nosecap and a stabilizing parachute assembly. A conical adapter section between the rocket motor and paylod sections contains the missile’s inertial navigation system and guidance electronics. When launched from submarine torpedo tubes the missile assembly also includes a watertight composite capsule surrounding the missile which provides environmental protection during submerged launch from a submarine torpedo tube and buoyancy to bring the weapon to the surface before the rocket motor fires. The missile’s rocket motor is 55 cm in diameter and 3.5 meters long and is constructed from filament wound graphite epoxy composite. The motor weighs 1,050 kg including 900 kg of composite propellant. The rocket motor burns for 25 seconds with a peak thrust of 100 kN, accelerating the missile to a burnout velocity of over mach 2.5 (750 m/s). The rear of the rocket motor includes four flip out tail fins for stabilization and is steered during rockrt motor burn by a turbo hydraulic thrust vector control system with a hydraulically actuated ball joint nozzle with +\- 10 thrust vector capability.

Guidance

Warhead

Flight Sequence
For submarine launch the encapsulated RBS 86 is loaded and fired like a conventional torpedo. Following ejection from the torpedo tube the missile continues forward for several meters until an umbilical breakwire connecting the missile to the torpedo tube is severed, causing the capsule to turn vertically and rise towards the surface. When an accelerometer inside the missile detects that the capsule has breached the surface the nose of the capsule is explosively ejected and the missile’s rocket motor is ignited, accelerating the missile out of the capsule and toward the target area. Following rocket motor burn the missile coats on a ballistic trajectory toward the target area. As the missile approaches the target area a set of drag flaps on the center adapter section are extended, slowing the missile to subsonic speeds before the adapter and rear rocket motor section of the missile are explosively separated from the forward payload section of the missile. The sidewalls of the payload section are then separated and the F3S Viperfish torpedo inside then deploys it’s attached parachute and descends to the sea surface. When the torpedo hits the water it’s aerodynamic nose cap shatters and it’s parachute detaches before it’s propulsion system is activated and it begins it search pattern.

by **The Technocratic Syndicalists** » Wed Oct 28, 2020 11:49 am

DWS 1000

General Characteristics:
Type:
Guided cluster bomb

Launch platform:
Aircraft

Guidance:
INS/GPS, Imaging infrared (IIR)
Physical Characteristics:
Weight:
1,000 kg

Length:
4.1 m

Diameter:
0.55 m

Payload:
DWS 1000A:
72x SB 8 Fragment Incendiary Shaped Charge submunitions

DWS 1000B:
36x ZEPL sensor fuzed anti-armor submunitions

Performance Characteristics:
CEP:
<3 m

Range:
130 km (Mach 0.9 release @ 12,000 meters

Overview:
The DWS 1000 is a family of fully autonomous standoff guided cluster glide bombs which are designed to enable standoff attacks against armor, air defense, and airfield targets outside the range of short and medium range air defense systems. The DWS 1000 consists of a common airframe and guidance section with an interchangeable center payload section which allows the weapon to configured with different cluster munitions payloads to defeat specific target types.

Airframe:
The DWS 1000 consists of a rectangular shaped unpowered glide body divided into three sections; a a faceted nose fairing that houses the weapon's seeker and guidance electronics, a rectangular center section with two fold out glide wings and the weapons cluster munition payload, and a tail section with four aerodynamic tail control surfaces actuated by an electro-mechanical tail control system. Virtually the entire weapon including the nose fairing, fuselage, wings, tail, and tail fins is constructed from vacuum assisted resin transfer molded (VARTM) graphite/epoxy and glass/epoxy composite which results in a low structural weight and along with the weapon's lack of propulsion results in a low radar cross section and infrared signature.

Guidance & Flight Sequence:
The DWS 1000 is guided by a combination IN/GPS midcourse guidance system and a scanning imaging infrared seeker in the nose of the munition which is used for target detection and automatic target recognition (ATR), submunition cueing, and additional point to point image-based terrain reference navigation. The weapon's midcourse guidance unit (MGU) consists of an SDI TNS 570 tactical inertial measurement unit, a C band LPI (Probability of Intercept) radar altimeter, 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 munition'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 guidance augmented by a cooled 640 x 480 element InSb imaging infrared (IIR) seeker operating in the MWIR (3– 5 µm) band which is mounted in the nose of the weapon. The seeker has a 10° instantaneous field of view and is mounted to a 2-axis stabilized gimbal driven by twin limited angle torque motors (LTA) which gives the seeker +/- 45° pointing capability in azimuth and +10°/- 30° in elevation. Images from the IIR seeker are processed using a multi-sensor signal processor (MSSP) in the weapon's guidance electronics section which provides real-time autonomous target recognition (ATR) and sensor management capability. The seeker is stabilized to the horizon using the 2-axis gimbal system with a strap-down stabilization algorithm which takes angular weapon position inputs from the IMU and gimbal position inputs from the encoders in the gimbal motors to command the gimbal torque motors to keep the seeker stabilized along the horizon as the weapon banks and maneuvers.

Following release from the aircraft the weapon uses it's INS/GPS system to navigate along a series of 3D waypoints to its specified target area On route to the designated target area the infrared seeker is used for midcourse position updates and generates three-dimensional line models of landmarks along the weapon's flight path which are then compared to images stored in the weapon before launch, allowing the weapon to determine its position and acting as enhancement to the missile's INS/GPS midcourse guidance system and enables the weapon to accurately navigate without GPS guidance signals if necessary. As the weapon approaches its designated target area it descends to an altitude of around 500 meters using its radar altimeter where the seeker is used in a pushbroom scan mode to sweep back and forth along either side of the weapon's ground track to scan for targets. Images from the IIR seeker are processed using a multi-sensor signal processor (MSSP) in the weapon's guidance electronics section which provides real-time autonomous target recognition (ATR) and sensor management capability. Potential targets in the scene are first ranged using using radar altimeter inputs, infrared sensor elevation angle, and stored digital map data. Targets in the scene are then classified through the use of a minimum average correlation energy (MACE) infrared signal processing algorithm which correlates each visible surface on detected targets with an onboard library of target profiles and is designed to recognize targets even when they are obscured by as much as 50%. Once a target or set of targets has been identified the weapon will initiate ejection of one or more submunitions from either side of the weapon to attack the target.

Warheads:
DWS 1000A:The DWS 1000A contains a payload of 72 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 72 sideways facing launch tubes (36 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.

DWS 1000B: The DWS 1000B contains a payload of 36 ZEPL sensor fuzed anti-armor submunitions and is optimized for attacking convoys of armored vehicles. The submunitions are contained in 36 sideways facing launch tubes (18 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 t self-destruct at an altitude of 10 meters, preventing it from becoming unexploded ordinance.

by **The Technocratic Syndicalists** » Sun Nov 15, 2020 9:11 pm

Sparrowhawk-100

General Characteristics:
Type:
loitering munition

Launch platform:
Portable launch tube

Guidance:
IR/EO, INS/GPS
Physical Characteristics:
Weight:
3.0 kg

Length:
0.8 m

Wingspan:
1.2 m

Warhead:
0.5 kg blast-fragmentation
Performance Characteristics:
Propulsion:
Electric motor

Maximum speed:
100 knots

Cruise speed:
60 knots

Range:
40 km

Endurance:
30 minutes

by **The Technocratic Syndicalists** » Mon Nov 23, 2020 3:21 pm

Sparrowhawk-200

General Characteristics:
Type:
Anti-armor loitering munition

Launch platform:
Portable launch tube

Guidance:
IR/EO, INS/GPS
Physical Characteristics:
Weight:
22.5 kg

Length:
1.3 m

Diameter:
0.12 m

Warhead:
4.0 kg tandem shaped charge
Performance Characteristics:
Propulsion:
Electric motor

Maximum speed:
100 knots

Cruise speed:
60 knots

Range:
40 km w/ 20 minute loiter

Endurance:
60 minutes

Overview:
The SDI Sparrowhawk is a tube launched, loitering munition with an anti-armor warhead designed by SDI Missiles & Fire Control System. The Sparrowhawk is packaged inside of a man portable self-contained launch tube assembly (LTA) which contains the munition and a pneumatic ejection system which deploys the munition from the tube. The Sparrowhawk munition itself posses up to an hour of flight endurance using an electric propulsion system with a low infrared and aural signatures and carries a multi-spectral electro-optical targeting sensor suite allowing the munition to act as portable intelligence, surveillance and reconnaissance (ISR) platform in addition to acting as a weapon. For engaging targets the munition carries a tandem shaped charge warhead with a fragmenting steel liner designed to be effective against both armored and unarmored vehicles, persoonel, and materiel targets. The complete Sparrowhawk munition system consists of a case containing twin launch tube assemblies and other case containing a touchscreen tablet based fire control unit (FCU) and a portable omni-directional datalink antenna system.

Airframe & Propulsion:
The Sparrowhawk munition features a cylindrical fuselage 12 centimeters in diameter and 130 centimeters long constructed from graphite/epoxy composite. The rear of the munition contains the propulsion section with an brushless permanent-magnet electric motor driving a two bladed pusher propeller with a design cruise speed of 60 knots (110 km/h) and a maximum terminal dive speed of 100 knots (185 km/h). The electric motor is supplied electricity by a high power density thermal battery located inside the missile's midsection which gives the munition a flight time of up to 1 hour. Lift is provided by a flip-out wing mounted to the top of midsection of the missile which springs out after the munition is ejected from the launch tube assembly. Steering is provided by four rear flip-out tailfins actuated using an electro-mechanical control actuation system (CAS) powered by the missile's battery. The nose of the munition contains the terminal seeker with a four-sensor 2-axis stabilized gimbal along with the missile's inertial measurement unit, GPS receiver, and digital autopilot system. The missile's shaped-charge warhead employs a main charge with a steel fragmentation liner located behind the battery and a smaller precursor charge located in the nose behind the gimbal assembly.

Guidance:
The Sparrowhawk is equipped with a 2-axis stabilized gimballed sensor suite with four electo-optical sensors; twin 4,608 × 3,288-pixel color CCD imagers with 1.2°- 56° FOV and up to 50x digital zoom, a 1280 x 960 pixel low-light television (LLTV) camera with 17° – 8.4° FOV, ,and an uncooled 640 x 512 pixel LWIR (long-wave infrared) imager with a fixed 32° FOV. The sensor head features +30° to -90° tilt capability and capable of rotating a full 360° with 2-axis active stabilization and 6-axis vibration isolation from the missile body. Imagery from the sensor suite is transmitted using an L band (1,625MHz to 1,725 MHz) encrypted data link system at up to 4.5 Mbps to the system's tablet based fire control unit (FCU) through a portable data link antenna connected to the tablet which lets the user select and designate targets for the munition to attack. Midcourse guidance is provided by a 6-axis strapdown inertial measurement unit (IMU) containing a 3-axis fiber optic gyro assembly and 3-axis MEMS (Micro Electro Mechanical System) silicon accelerometer which is coupled to a GPS unit with a 24 channel SAASM (Selective Availability Anti-spoofing Module) based anti-jam GPS receiver.

Warhead & Fuzing:
The Sparrowhawk munition is equipped with a 4.0 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 a molybdenum shaped charge liner liner, 1.1 kilograms of polymer bonded HMX explosive (95.5% HMX, 4.5% Estane and 5702-Fl plastic binder), a syntactic foam wave-shaper, central and peripheral detonators, and an electro-mechanical safe & arm device (ESAD). A precursor warhead also employing a molybdenum shaped charge liner and polymer bonded HMX explosive is located ahead of the main warhead in the seeker section of the projectile 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 nose mounted impact switch which triggers the the peripheral detonators in order to create a high speed, small diameter penetrating jet capable of penetrating in excess of 900 mm RHA after ERA. For attacking unarmored or lighly armored targets targets a height-of-burst proximity sensor in the nose of the munition is used to initiate the central and peripheral detonators which causes the main warhead's molybdenum shaped charge liner and high-fragmentation steel case to break up and release over 4,500 high-velocity fragments, creating a lethal-zone to exposed personnel over 20 meters in diameter.

by **The Technocratic Syndicalists** » Sun Nov 29, 2020 5:13 pm

Sparrowhawk-400

General Characteristics:
Type:
Anti-armor loitering munition

Launch platform:
Vehicle, ship, helicopter

Guidance:
IR/EO, INS/GPS
Physical Characteristics:
Weight:
45.0 kg

Length:
2.1 m

Wingspan:
2.4 m

Diameter:
0.18 m

Warhead:
9.0 kg tandem shaped charge
Performance Characteristics:
Propulsion:
4.5 kw EFI piston engine

Maximum speed:
115 knots

Cruise speed:
85 knots

Range:
200 km

Endurance:
6 hours

Overview:
The SDI Sparrowhawk-400 is a loitering munition with an anti-armor warhead designed by SDI Missiles & Fire Control System. The Sparrowhawk-400 munition itself posses up to 6 hours of flight endurance using anpiston engine based propulsion system and carries a multi-spectral electro-optical targeting sensor suite allowing the munition to act as portable intelligence, surveillance and reconnaissance (ISR) platform in addition to acting as a weapon. For engaging targets the munition carries a tandem shaped charge warhead with a fragmenting steel liner designed to be effective against both armored and unarmored vehicles, personnel, and materiel targets. The complete Sparrowhawk-400 munition system consists of two Sparrowhawk-400 munitions and a case containing a touchscreen tablet based fire control unit (FCU) and a portable omni-directional datalink antenna system.

Airframe & Propulsion:
The Sparrowhawk-400 munition features a cylindrical fuselage 18 centimeters in diameter and 210 centimeters long constructed from graphite/epoxy composite. The rear of the munition contains the propulsion section with a 4.5 kw electronic fuel injection (EFI) 4-stroke 2-cylinder piston engine driving a two bladed pusher propeller with a design cruise speed of 85 knots and a maximum terminal dive speed of 115 knots. Lift is provided by twin flip-out wings mounted to the top of midsection of the missile which spring out as the munition is launched. Steering is provided by four rear flip-out tailfins actuated using an electro-mechanical control actuation system (CAS). The nose of the munition contains the terminal seeker with a multi-sensor two-axis stabilized gimbal along with the missile's inertial measurement unit, GPS receiver, and digital autopilot system. The missile's shaped-charge warhead employs a main charge with a steel fragmentation liner located behind the missile's central fuel tank and a smaller precursor charge located in the nose behind the gimbal assembly.

Guidance:
The Sparrowhawk-400 is equipped with a 2-axis stabilized gimballed sensor suite with two electo-optical sensors; a 1280 x 720 pixel color CCD imager with 1.1°- 31.5° FOV and up to 12x digital zoom and a cooled 640 x 512 pixel MWIR (mid-wave infrared) imager with a 1.6°- 22° FOV. The sensor head features +80° to -45° tilt capability and capable of rotating a full 360° with 2-axis active stabilization and 6-axis vibration isolation from the missile body. Imagery from the sensor suite is transmitted using an L band (1,625MHz to 1,725 MHz) encrypted data link system at up to 4.5 Mbps to the system's tablet based fire control unit (FCU) through a portable data link antenna connected to the tablet which lets the user select and designate targets for the munition to attack. Midcourse guidance is provided by a 6-axis strapdown inertial measurement unit (IMU) containing a 3-axis fiber optic gyro assembly and 3-axis MEMS (Micro Electro Mechanical System) silicon accelerometer which is coupled to a GPS unit with a 24 channel SAASM (Selective Availability Anti-spoofing Module) based anti-jam GPS receiver. The munition's autopilot is can contain up to 100 waypoints each programmed with specific GPS position, altitude, and velocity which can be and uploaded and modified in mid flight.

Warhead & Fuzing:
The Sparrowhawk-400 munition 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 vehicles and structure targets. The main warhead consists of an HF-1 high-fragmenting steel case containing 5.7 kilograms of HMX based polymer-bonded explosive (95% HMX, 2.5% estane, 2.5% BDNPA), 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** » Mon Feb 07, 2022 8:43 pm

RBS 99 Bolide

General Characteristics:
Type:
Tactical ballistic missile

Launch platform:
TEL

Guidance:
Synthetic-aperture radar (SAR), INS/GPS, 2-way RF datalink
Physical Characteristics:
Weight:
4,800 kg

Length:
8.1 m

Diameter:
1.0 m

Warhead:
Rb 99A:
20x terminally guided submunitions (TGSM)

Rb 99B:
68x kinetic energy penetrator (KEP) submunitions

Rb 99C:
500 kg unitary penetrator
Performance Characteristics:
Propulsion:
Solid fuel rocket

Speed:
Mach 9 (2,700 m/s) burnout

CEP:
<1 m (<3m with GPS/INS only)

Flight ceiling:
200 km

Range:
100 to 800 km

Overview:
The RBS 99 Bolide is a mobile ballistic missile system designed by SDI Missile Systems designed to engage high value tactical and strategic targets deep in enemy territory. The RBS 99 is intended to be used with the A 13 Vanguard battlefield surveillance aircraft to form part of a reconnaissance-strike system for attacking massed armor formations and mobile surface-to-surface and surface-to-air units deep behind enemy lines. The RBS 99 comes in three variants, the RBS 99A which carries a payload of terminally guided anti-armor submunition payload for attacking armored formations, mobile surface to surface missile launchers and mobile air and missile defense systems, the RBS 99B which carries a payload of concrete penetrating submunitions for attacking airfields, and the RBS 99C which carries a unitary penetrator intended for attacking warships, structures, infrastructure targets, and hardened and deeply buried targets. All variants share the same basic propulsion section with a detachable maneuvering reentry vehicle (MaRV) section interchangeable between all three variants, allowing missiles to be rapidly reconfigured with a different warhead in the field. When combined with target designation capability from the A 13 Vanguard battlefield surveillance aircraft the RBS 99 forms part of a reconnaissance-strike system for attacking massed armor formations, mobile surface-to-surface and surface-to-air units, and other mobile and relocatable targets deep behind enemy lines.

The components of the RBS 99 system include the Rb 99 missile, transporter-erector-launcher vehicle (SDI HTTS chassis) with two missiles, transporter and loader vehicle (SDI HTTS chassis) with two reloads each and a 30 kW generator and hydraulic crane, command vehicle, (GdW 30 chassis), mobile communication center vehicle, (GdW 30 chassis), and mobile workshop vehicle (SDI HTTS chassis). A complete RBS 81 battery consists of eight transporter-erector-launcher vehicles, eight transporter and loader vehicles, two firing platoon command vehicles, one battery command vehicle, one mobile communication center vehicle, and one mobile workshop vehicle.

Airframe & Propulsion:
The Rb 99 missile consists of four sections: a propulsion section and a nd a maneuvering reentry vehicle (MARV) section. The maneuvering reentry vehicle (MARV) is further divided into a guidance and control/adapter (G&C/A) section, warhead section, and radar section. The propulsion section consist of a solid rocket motor with forward and aft skirts, the forward skirt mating to the reentry vehicle. The propulsion section contains 3,600 kilograms of high energy density composite solid propellant with a 90% solid loading consisting of 20% aluminum fuel, 24% HMX, 46% AP oxidizer, and 10% HTPB and burns for 60 seconds with a peak thrust of 170 kN and a sea level specific impulse of 280 seconds, accelerating the missile to a burnout velocity of around mach 9 (2,700 m/s). The forward skirt contains three thrust termination ports spaced evenly around the motor casing which are activated by the missile's guidance and control computer after reentry vehicle separation, proving a reverse thrust in the propulsions section to allow the reentry vehicle to cleanly separate from the propulsion section. The aft skirt contains four control fins, two fixed fins and two hydraulically actuated fins to provide first stage roll control, and a gimballed nozzle with two hydraulic actuators which provides pitch and yaw control. The motor case is made from graphite/epoxy composite with the motor nozzle constructed from triaxially braided 3-D carbon-carbon composite. Both forward and aft skirts are made from 7075 aluminum alloy.

The missiles' maneuvering reentry vehicle consists of an adaptor, guidance and control section, warhead section, and radar section. The adaptor section connects the reentry vehicle to the propulsion section and consists of conical 7075 aluminum alloy structure with a heat-resistant phenolic coating. The guidance and control section contains the missile's guidance electronics unit (GEU), control fins system, missile thermal battery, reaction control system, and reentry vehicle separation system. The guidance electronics unit controls all functions of the missile during flight and contains the missile's flight computer, synthetic aperture radar (SAR) processor, datalink transceiver unit, 6-axis ring laser gyro (RLG) inertial measurement unit (IMU), and 24 channel dual-frequency Selective Availability Anti-spoofing Module (SAASM) based GPS receiver. The control fin system consists of four hydraulically actuated control fins which provide reentry vehicle control during the terminal stage of flight. The reaction control system consists of a total of 10 warm-gas attitude-control thrusters placed behind the control fins which provide reentry vehicle roll, pitch, and yaw control during the exo-atmospheric midcourse phase of flight. Behind the reaction control system at the aft end of the reentry vehicle is the separation system which contains a linear shaped charge (LSC) ring assembly which separates the reentry vehicle from the adaptor section on the command of the missile's flight computer. Forward of the guidance and control section is the warhead section which contains cables that connect the G&C section to radar section and depending on the missile variant contains either a cluster munition payload or a unitary penetrator warhead. Forward of the warhead section is the radar section which contains a pair of wideband conformal datalink antennas along with the missile's synthetic aperture radar antenna unit which is enclosed in a high temperature reaction-sintered silicon nitride (Si3N4) radome.

Guidance & Flight Sequence:
The Rb 99 missile is guided by a terminal linear frequency modulated - continuous wave (LFM-CW) synthetic aperture radar (SAR) seeker coupled with an INS/GPS midcourse guidance unit and a two-way datalink which allows the missile to be retargeted in flight by an A 13 Aircraft. The synthetic aperture radar (SAR) seeker is contained inside a radome in the radar section of the reentry vehicle and consists of a stabilized antenna unit with a 17 cm diameter antenna operating in the X-band (9.3–9.6 GHz). The antenna is coupled with a strapdown 6-axis fiber-optic IMU to compensate for motion by the reentry vehicle during seeker operation. Guidance during the boost and midcourse phases of flight is provided 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 contained in the missile's guidance electronics unit section which provides accurate all-weather midcourse guidance for the missile. In case of synthetic aperture radar (SAR) seeker failure the INS/GPS guidance system can also be used for terminal guidance against stationary geolocated targets or a combination of INS/GPS and external command guidance by an A 13 Aircraft against mobile targets with a slight reduction in accuracy.

After ignition the missile's inertial measurement unit is used to maneuver it onto a precomputed firing azimuth with missile pitch and yaw control provided by the gimballed thrust-vector control (TVC) nozzle and roll control provided by the propulsion section aft control fins. The propulsion section motor then burns until the desired burn out velocity is achieved where the reentry vehicle separation system and thrust reversal systems are activated, separating the reentry vehicle from the propulsion section. Following separation from the propulsion section the reaction control thrusters in the reentry vehicle are used to maintain attitude control and orient the reentry vehicle for atmospheric reentry. During the phase the reentry vehicle can also receive guidance updates from an A 13 Aircraft using the wideband conformal datalink antennas on the reentry vehicle, allowing the missile to be retargeted in flight. When the reentry vehicle enters the denser part of the atmosphere the control fins are used for control where at an altitude of around 30 kilometers the reentry preforms a high-g pull-up maneuver, glides to the target area, and then over the target performs a pull-down mabuever and dives down on the target at a near vertical area. During the final dive down onto the target the synthetic aperture radar (SAR) seeker in the nose of the reentry vehicle is activated and performs a <1 meter resolution 5 x 5 kilometer squint mode stripmap scan of the terrain under the path of the reentry vehicle. The synthetic aperture radar (SAR) processor in the missile's guidance electronics unit (GEU) then compares the scene generated by the seeker to a target reference template stored in the computers memory to identify the location of the target within the scene. When the target has been detected and located in the scene the guidance computer then computes the necessary trajectory corrections to impact the target and applies them using the control fins on the reentry vehicle. Should the seeker malfunction or fail to squire the target the missile can also be command guided in the terminal phase by an A 13 Aircraft using its FMG 110 radar to track both the missile and intended target and continually transmit guidance updates to the missile through its datalink system.

Warhead
Rb 99A: The Rb 99A is designed primarily to attack columns of armored vehicles, MLRS units, surface to air and surface to surface missile systems and contains a payload of 20 terminally guided submunitions (TGSMs). The submunitions are contained in two radial rows, one of 12 submunitions and one of 8 submunitions, surrounding a central air bag dispenser system mounted to central structural tunnel which connects the radar and guidance and control sections of the reentry vehicle. 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 reentry vehicle in two concentric rows. Each TGSM is 140 mm in diameter and 900 mm long with a weight of 20.0 kiligrams 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 and capable of penetrating over 1,100 mm of RHA. 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 99B: The Rb 99B is intended to attack airfields and contains a payload of 68 energy penetrator (KEP) submunitions designed to create large craters in runways. The KEP submunitions are contained in three stacked radial rows in the warhead section of the missile surrounding the central structural tunnel which connects the radar and guidance and control sections of the reentry vehicle. When over the target an an altitude of around 1,700 meters the missile's flight computer commands the reentry vehicle's guidance fins to deflect in order to spin up and slow the reentry vehicle where at an altitude of around 1,000 meters the guidance 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 and dispenses the submunitions using the centrifugal force from the reentry vehicle, releasing the submunitions in three concentric rows which then impact the runway in three concentric elliptical rings. Each KEP submunition is 70 mm in diameter, 860 mm long, weighs 8.5 kilograms, and consists of a penetrating warhead with a hardened tool steel case filled with 1.6 kilograms of polymer bonded aluminized RDX explosive (65% RDX, 20% Al, 15% HTPB) connected to a rear tailfin kit which deploys after submunition ejection to stabilize each KEP before impact. The warhead of the KEP is initiated using a piezoelectric point initiating, base detonating (PIBD) delay fuze which explodes after impact, creating a large crater in the concrete runway.

Rb 99C: The Rb 99C replaces the cluster munition dispenser warhead of the A and B variants with a 500 kilogram penetrating blast-fragmentation warhead which is intended for attacking hardended and deeply buried targets The warhead consists of a streamlined steel case 2.4 meters long and 37 centimeters in diameter constructed from 3.5 GPA (500,000 psi) tensile strength nickel-molybdenum-cobalt maraging steel (8Ni-14Mo-20Co-Fe) filled with 125 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 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. When used against hard and deeply buried targets the high supersonic impact velocity of the missile allows the warhead to penetrate over 6 meters of 34.5 MPa reinforced concrete before exploding.

by **The Technocratic Syndicalists** » Tue May 10, 2022 7:55 pm

RBS 210 Saber

General Characteristics:
Type:
Hypersonic boost-glide missile

Launch platform:
TEL

Guidance:
INS/GPS
Physical Characteristics:
Weight:
3,800 kg

Length:
8.2 m

Diameter:
0.8 m

Warhead:
6x terminally guided submunitions (TGSM)

Performance Characteristics:
Propulsion:
two-stage solid fuel rocket

Speed:
Mach 10 (3,000 m/s) burnout

CEP:
3 m

Flight ceiling:
35 km

Range:
2,000 km

Overview:
The RBS 210 Saber is a hypersonic boost-glide missile system designed by SDI Missile Systems designed to engage high value tactical and strategic targets deep in enemy territory. The missile consists of a two-stage solid fuel rocket booster attached to a maneuvering hypersonic glide vehicle which carries a payload of terminally guided submunitions attacking mobile surface to surface missile launchers and mobile air and missile defense systems

Airframe & Propulsion:
The RBS 210 missile consists of five sections, a first stage propulsion section, second stage propulsion section, adapter, hypersonic glide vehicle (HGV), and ejectable nosecone . The first stage propulsion section of the missile consists of a solid fuel rocket motor with attached forward and aft skirts skirt. The forward skirt mates to the to the second stage propulsion system while the aft skirt contains four movable control fins and a gimballed thrust vector control (TVC) nozzle with two electrohydraulic actuator which provides pitch and yaw control during first stage burn. The first stage motor is constructed from transverse wound carbon-fiber-reinforced polyetheretherketone (PEEK) with an internal aramid-filled ethylene propylene diene monomer (EPDM) insulation liner and contains contains 1,800 kilograms of high energy density composite solid propellant with a 90% solid loading consisting of 20% aluminum fuel, 24% HMX, 46% AP oxidizer, and 10% HTPB binder. The first stage burns or 30 seconds and accelerates the missile to a nominal burnout velocity of 1.5 km/s.

The second stage propulsion section features a variable burn time and accelerates the missiles to the required burnout velocity computed by the guidance system as a function of target range and planned trajectory. The first stage the second stage consists of a solid propellant rocket motor with forward and aft skirts. The forward skirt of the second stage contains contains three thrust termination ports spaced evenly around the forward motor casing which are activated by the missile's guidance computer after the desired burnout velocity has been reached, extinguishing the second stage motor and proving a reverse thrust in the second stage motor which allow the glide vehicle to cleanly separate from the second stage. Like the first stage the aft skirt houses four movable control fins and a gimballed thrust vector control (TVC) nozzle with two electrohydraulic actuator which provides pitch and yaw control during first stage burn. The second stage is constructed from transverse wound carbon-fiber-reinforced polyetheretherketone (PEEK) with an internal aramid-filled ethylene propylene diene monomer (EPDM) insulation liner with an additional external sacrificial aramid fiber overwrap and contains 1,100 kilograms of 20% aluminum, 24% HMX, 46% AP, and 10% HTPB composite propellant. The second stage motor burns for a maximum of 30 seconds and accelerates the missiles to a maximum burnout velocity of 3.0 km/s at an altitude of 35,000 meters where the missile's hypersonic glide vehicle (HGV) separates from the second stage and begins its hypersonic glide towards the target

The missile's hypersonic glide vehicle (HGV) consists of a conical shaped vehicle with four rear mounted control fins which contains the missile's guidance and navigation system and submunition payload. The hypersonic glide vehicle is covered by a nose cone ejected following second stage burn which serves to protect the glide vehicle from environmental or mechanical damage during handling and loading. The structure of the glide vehicle is contracted from Ti-6Al-4V titanium alloy with a hafnium carbide (HfC) coated 3-D carbon/carbon phenolic heatshield with internal carbon foam insulation which is bonded to the underlying titanium glide vehicle structure with pyrolytic graphite supports. The four control fins are constructed from carbon fiber reinforced silicon carbide (C/SiC) and are actuated by a set of four electro-mechanical actuators inside the glide vehicle body to provide roll, pitch, and yaw control during flight. Behind the nose of the glide vehicle contains the missile's guidance and navigation section which contains the missile flight computer, twin 6-axis inertial measurement units (IMUs), and 24 channel dual-frequency Selective Availability Anti-spoofing Module (SAASM) based GPS receiver. Aft of the guidance section is the payload section which contains six submunitions inside launch canisters which are ejected from the aft of the glide vehicle in the terminal phase of flight.

Guidance & Flight Sequence:
The reentry vehicle is guided in flight through a combination GPS/INS system which combines twin inertial measurement units employing 3-axis laser-ring gyros (LRGs) and 3-axis pendulous integrating gyroscopic accelerometers which are coupled to a Selective Availability Anti-spoofing Module (SAASM) based GPS receiver with four dual frequency (L1/L2) conformal wideband GPS antenna blended into the rear surface of the glide vehicle. The INS/GPS guidance is coupled with the ability to employ external command guidance by an A 13 Aircraft against mobile targets employing a pair of 1-way datalink antennas blended into the aft end of the glide vehicle alongside the GPS antennas.

After ignition the missile's inertial measurement unit is used to maneuver it onto a precomputed firing azimuth with missile pitch and yaw control provided by the gimballed thrust-vector control (TVC) nozzle and roll control provided by the propulsion section aft control fins. Following first stage burnout the missile is then programmed to enter short coast period before the missile guidance computer issues the first stage separation signal. Following reception of the first stage separation command a linear shaped charge array in the aft skirt of the second stage is detonated, separating the second stage from the first stage. The second stage is then ignited, accelerating the missile along its intended flight path. When the guidance computer determines that the desired burnout velocity, altitude, and burnout angle have been reached the guidance computer issues a second stage separation signal which simulatrnosuly activates he thrust termination ports in the second stage motor and detonates a linear shaped charge array in the glide vehicle adapter section, separating the glide vehicle from the second stage.

On a maximum range trajectory the hypersonic glide vehicle is released from the second stage of the missile at a velocity of around 3.0 kilometers per second at an altitude of approximately 35,000 meters where the vehicle orients itself using it's INS and establishes an optimal angle of attack before beginning its hypersonic glide towards the intended target area. After gliding to the intended target area the glide vehicle performs a high-G pull-down maneuver from its final glide altitude of around 30,000 meters and dives down sharply towards its intended target area where the vehicle performs an aerobraking maneuver to decelerate to low supersonic speeds where the terminally guided submunition payload is then released.

Warhead
The Rb 210is designed primarily to attack multiple rocket launcher, surface to air and surface to surface missile systems and contains a payload of six terminally guided submunitions (TGSMs). The submunitions are contained in a single radial rows of 6 submunition each contained in a pneumatic launch tube which ejects the submunition from the rear of the hypersonic glide vehicle at an altitude between 2,000 and 4,000 meters above ground level. 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 and capable of penetrating over 1,000 mm of RHA. 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.

by **The Technocratic Syndicalists** » Tue Jun 14, 2022 5:29 pm

Rb 81

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

Launch platform:
TEL, VLS

Guidance:
Ka band active radar homing, INS/GPS, RF datalink
Physical Characteristics:
Weight:
320 kg

Length:
4.5 m

Diameter:
250 mm

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

Speed:
Mach 4.0

Maneuverability:
60 G

Operational range:
1-120 km

Intercept altitude:
0-25 km

Overview:
The Rb 81 is a medium range surface-to-air missile designed by SDI Missile Systems. The Rb 81 forms part of SDI's RBS 81 medium range air and missile defense system and provides all-weather intercept capability against fixed and rotary wing aircraft, cruise missiles, tactical ballistic missiles, and loitering munitions.

Airframe & Propulsion:
The Rb 81 missile consists of four sections; guidance section with active radar seeker seeker assembly, 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 25 centimeter diameter dual-pulse rocket motor consists of two radial burning propellant grains separated by a flexible elastomeric bulkhead, a blast tube, and a nozzle. The motor features a 50/50 propellant split between the first and second pulses with both motor pulses providing over 35 kN of thrust and employing SDI's 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 specific impulse and burn rate, low impact and thermal sensitivity, and low exhaust signature. The first pulse used to accelerate the missile toward the target while the second pulse is to provide thrust to maneuver the missile for terminal homing. The ignition delay between missile pulses is set by the missile's digital autopilot and varies with the missile's trajectory. For short range high-off boresight engagements an all-boost burn profile with no delay between pulses is used while for longer ranged engagements a lofted trajectory with a boost-coast-boost burn profile is used. The motor casing is constructed from filament-wound graphite reinforced polyetheretherketone (PEEK) with an internal aramid-filled ethylene propylene diene monomer (EPDM) insulation layer. Control is provided by an integrated aerofin/thrust vector control system with four tail fins actuated by compact electro-three phase brushless servomotors and four jet vane actuators which provide +/- 20° thrust vectoring capability. The integrated aerofin/thrust vector control system give the missile up to 60 g of lateral acceleration capability, 120° angle-of-attack capability, and a turn rate of up to 100° per second.

Guidance
The Rb 81 missile is equipped with a Ka band (34 - 36 GHz) active radar seeker. The seeker employs a solid state GaN MMIC power amplifier and receiver, and a strapdown passive electronically scanned antenna composed of 1,000 separate radiating elements connected to a MEMS based phase shifter which can be electronically scanned +/- 60° in azimuth and elevation. The guidance section of the missile is also equipped with a strapdown tactical grade IMU containing 3-axis fiber-optic gyro (FOG) and 3-axis solid-state silicon accelerometers which are combined with a 24 channel dual-frequency *L1/L2) SAASM based GPS receiver to provide midcourse phase guidance for the missile.

Warhead
The Rb 81 missile contains a 20 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 proximity fuze in the mid section of the missile or an impact fuze in the nose behind the seeker.

by **The Technocratic Syndicalists** » Wed Aug 10, 2022 9:31 am

Rb 82

General Characteristics:
Type:
Anti-satellite missile

Launch platform:
TEL

Guidance:
imaging infrared (IIR), RF datalink
Physical Characteristics:
Weight:
10,400 kg

Length:
12.0 m

Diameter:
1.0 m

Warhead:
75 kg kinetic kill vehicle
Performance Characteristics:
Propulsion:
3-stage solid-fuel rocket

Speed:
8.0 km/s burnout

Range:
5,000 km

Intercept Altitude:
100 to 3,000 km

Overview:
The Rb 82 is a TEL launched anti-satellite missile with the capability to destroy satellites in low-earth orbit at altitudes up to 3,000 kilometers.

Airframe & Propulsion:
The Rb 82 consists of a multiple stage solid fuel rocket motor which is designed to accelerate an exo-atmospheric kill to sufficient velocity to negate target satellites in orbit, an exoatmospheric kill vehicle, kill vehicle shroud, and a launch canister with integral hot gas ejection system. The missile's propulsion system consists of a 3-stage solid-fuel missile employing filament wound graphite/epoxy motors with high-performance composite 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 vacuum 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. The third stage motor is 0.56 meters in diameter, 1.0 meters long, has a gross mass of 285 kilograms including 225 kilograms of propellant. The third stage is a triple-pulse motor with three 10-second burns each with a peak thrust of 50 kN and a vaccum specific impulse of 290 s and provides additional acceleration and divert capability for the kill vehicle. The second and third stages feature 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 a warm-gas system (WGS) using solid-propellant gas generators and nozzles which provide roll, pitch, and yaw control during second and third stage motor burns. All stages 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 3-D carbon-carbon composite and each stage feature gimballed thrust-vector control using an electro-mechanically actuated ball nozzle joint with +/- 7.5 degree thrust vectoring capability.

Kill vehicle:
The Rb 82 employs an exoatmospheric kill vehicle (EKV) which is designed to impact and destroy satellites in orbit. The kill vehicle elements include the seeker assembly, GN&C system, downlink communication system, airborne power system, propulsion system, and the kill enhancement device (KED). The kill vehicle is fully autonomous and is designed to autonomously acquire and track designated target satellite, selecting a desired impact aimpoint on the target, and downlinking kill vehicle health and status, and transmitting mission downlink telemetry back to the ground command element of the launcher battery.

The seeker assembly consists of a the seeker optical telescope assembly and the seeker signal processor. The optical telescope assembly employs a Schmidt–Cassegrain telescope with a 30 cm diameter aperture which contains a 256 × 256 pixel quantum-well infrared photodetector (QWIP) focal plane array detector which operates simultaneously in the MWIR (3 to 5 µm) and LWIR (8 to 12 µm) bands and is cooled during operation to 100 K using a nitrogen gas blowdown system. The seeker also acts as a star tracker and is designed to provide stellar alignment to the kill vehicle prior to third stage separation. The seeker signal processor receives digital signal inputs from the FPA and uses them to detect and track targets, identify the kill vehicle aimpoint on the target, and transfer measurements of the angular position of the tracked target satellite relative to the optical axis to the kill vehicle's guidance, navigation and control (GN&C) system. The guidance, navigation and control (GN&C) system consists of a kill vehicle computer system (KVCS) and a 6-axis inertial measurement unit (IMU). The kill vehicle computer system receives signal inputs from the seeker signal processor and the IMU and is used to guide and control the kill vehicle during flight and to command the booster stack during launch and interceptor staging. The IMU is 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 KV downlink system consists of a Ka-band (26 GHz) antenna assembly and a downlink communications module which transmits data to a relay satellite for communication with the ground. The power subsystem for the kill vehicle consists of power converters, power distribution harness, and a thermal battery providing for 1,100 seconds of kill vehicle operation.

The kill vehicle's propulsion section is mounted around the midsection of the kill vehicle body and consists of divert thrusters, attitude control thrusters, and propellant tanks. The kill vehicle has four divert thrusters which provide the kill vehicle with up to 15 g of lateral acceleration and eight attitude control system (ACS) thrusters with four hypergolic ACs thrusters for high impulse attitude control and four helium cold-gas thrusters for low impulse attitude control. 20 kilograms of hydrazine (N2H4) and chlorine pentafluoride (ClF5) hypergolic propellant for the divert and attitude control thrusters are stored in four composite overwrapped pressure vessel (COPV) tanks around the kill vehicle midsection which gives the kill vehicle up to 1,000 m/sec of divert capability. The kill enhancement device (KED) is mounted to the rear of the kill vehicle and consists of a uniform pattern of high density tungsten pellets embedded in a thin mylar membrane supported by a lightweight, inflatable tubular frame which is deployed several seconds before impact in provide additional penetration and crushing of the target satellite structure and severing of critical power or sensor appendages.

by **The Technocratic Syndicalists** » Sun Jul 02, 2023 10:51 am

RBS 118 Lightbearer

General Characteristics:
Type:
Submarine launched ballistic missile (SLBM)

Launch platform:
Submarine

Guidance:
Stellar-inertial (missile), terminal fix system (reentry vehicles)
Physical Characteristics:
Weight:
68,000 kg

Length:
13.5 m

Diameter:
2.3 m

Warhead:
4-8 SDI maneuvering reentry vehicles with SG 90 nuclear warheads, 500 kt each
Performance Characteristics:
Propulsion:
3-stage solid-fuel rocket

Speed:
Mach 25 (7.5 km/s) burnout

Range:
8 warheads:
8,000 km
6 warheads:
9,500 km
4 warheads:
12,000 km
Accuracy:
<10 m CEP

Overview:
The RBS 118 is a submarine launched ballistic missile designed by SDI Missiles & Fire Control which is intended to equip SDI's Erebus class of nuclear ballistic missile submarines. The RBS 118 is an advanced three stage solid fuel missile which carried a payload of up to eight terminally guided maneuvering reentry vehicles equipped with 500 kiloton thermonuclear warheads which provide terminal maneuver capability to evade terminal anti-ballistic missile interceptor systems and very low CEP to effectively destroy hardened and deeply buried missile silos and command bunkers.

Airframe & Propulsion:
The RBS 118 is a three stage missile which consists of the first stage rocket motor, interstage, second stage rocket motor, post boost vehicle, third stage rocket motor, nose fairing, and nose cap with extending aerospike. All primary structures of the missile including the first and second stage motor cases, interstate, and equipment section are constructed from filament wound graphite/epoxy composite. The first stage includes the first stage rocket motor, first stage hydraulic thrust vector control (TVC) system, and first stage fiber-optic based laser ordnance firing system. The interstage section connects the first and second rocket rocket stages and contains electrical harnesses and stage separation equipment. The second stage section includes the second stage rocket motor, second stage hydraulic thrust vector control (TVC) system, and second stage fiber-optic based laser ordnance firing system. The post boost vehicle acts as the structural support between the aft end of the nose fairing and the forward end of the second stage and contains the missile's guidance and control electronics, post-boost propulsion system, and reentry subsystem which consists of penetration aids and up to eight reentry vehicle assemblies attached with four bolts to a release assembly mounted to the equipment section. The third stage is contained within the post boost vehicle and consists of the third stage rocket motor, third stage hydraulic thrust vector control (TVC) system, and third stage fiber-optic based laser ordnance firing system. The thirst stage is connected using a graphite/epoxy eject cylinder to the center of the post boost vehicle and separates from the post boost vehicle using a solid propellant eject motor recessed into the forward dome of the third stage rocket motor which pushes the third stage motor aft and separates it from the equipment stage following third stage motor burn. The graphite/epoxy composite nose fairing section covers the reentry vehicles and the forward portion of the TS motor and consists of a primary structure split into two halves with two jettison rocket motors and a locking mechanism. The nose cap assembly at the forward end of the nose fairing houses an extendable aerospike which is extended during the initial portion of flight to reduce aerodynamic drag.

The three solid fuel rocket stages employ filament wound graphite/epoxy motor casings containing a high-performance composite propellant with a 90% solid loading consisting of 20% aluminum fuel, 25% HNIW (Hexanitrohexaazaisowurtzitane) high-energy oxidizer, 45% aAmmonium perchlorate (AP) oxidizer, and 10% HTPB binder. The first stage is 2.3 meters in diameter, 7.5 meters long, and has a loaded mass of 47,000 kg including 44,500 kg of propellant and burns for 60 seconds with a peak thrust of 1,900 kN. The second stage is 2.3 meters in diameter, 3.0 meters in length, and has a loaded mass of 14,000 kg including 13,250 kg of propellant and burns for 60 seconds with a peak thrust of 700 kN. The third stage is 0.9 meters in diameter and 3.3 meters long and has a loaded mass of 2,600 kg including 2,300 kg of propellant and burns for 40 seconds with a peak thrust of 150 kN. The throat and nozzle of each motor is constructed from triaxially braided 4D carbon-carbon composite with each stage featuring gimballed thrust-vector control using an hydraulically actuated ball nozzle joints with an omnivector flexseal connected to two independent turbo-hydraulic systems providing +/- 7.5°thrust vectoring capability for each side. The second stage and third stage additionally feature carbon-carbon composite extendable nozzle sections to increase their expansion ratio and vacuum specific impulse. Both first and second stages feature identical hydraulic systems which consists of a solid propellant gas generator providing high temperature (1200°C) gas to a single stage axial turbine which directly drives a centrifugal pump at a speed of 100,000-130,000 RPM which in turns provides high pressure hydraulic fluid to a pair of hydraulic servo actuators which actuate each nozzle. Both first and second stages also feature identical attitude control systems consisting of four solid propellant gas generators which feed a total of 16 nozzles (four forward, four aft, eight roll) on the first and second stages. The post boost vehicle includes a post-boost propulsion system with two solid propellant gas generators containing 300 kg of propellant feeding a total of four divert thrusters and six attitude control motors with variable thrust pintle nozzles which are capable of producing up to 10 kN of axial thrust with a maximum burn time of 160 seconds for executing post-boost maneuvers.

Guidance:
The RBS 118 missile is guided by an SDI TNS 60 stellar-inertial guidance unit consisting of an inertial measurement unit (IMU) assembly housing stabilized inertial and stellar sensors. The inertial measurement unit is a spherical 4-gimbal stellar-inertial IMU which contains two twin-axis gyros, three pendulous integrating gyro accelerometers, an optical telescope, and a CCD stellar detector. The four gimbals are constructed of hollow aluminum and are designed to equalize heat transfer from the structure to the inner stable member at all gimbal angles. the spherical case is sealed with nitrogen gas at sea-level atmospheric pressure which provides the necessary heat dissipation for the inner IMU element. The inner stable member of the IMU is constructed from isostatically pressed beryllium and contains twin two-axis dry tuned gyros and three orthogonally mounted pendulous integrating gyro accelerometers (PIGAs) which sense missile angular and linear acceleration in the x,y, and z planes. The inner stable member also contains the stellar sensor assembly which consists of a 5 cm aperture cassegrainian reflector telescope with silver coated beryllium primary and secondary mirrors and a 90 x 90 pixel CCD detector array connected to a thermal electric cooler. The guidance electronics assembly contains four independent digital computers for missile guidance correction computing and is connected to the IMU assembly using four four fiber optic data buses. The IMU is mounted to the equipment section of the missile using shock absorbing mounts consisting of large diameter silicon rubber rings fused to a shock mount structure which is attached to the equipment section of the missile.

The missile's eight maneuvering reentry vehicles feature an inertial navigation system coupled to an SDI terrain fix system (TFS) which provides terrain based position and velocity updates to the vehicle's guidance computer as it approaches the target. The vehicle's inertial guidance system consists of an SDI TNS 1320 strategic grade inertial measurement unit, a radiation and shock hardened strapdown inertial measurement unit installed at the base of the vehicle employing laser ring gyros (RLGs) and pendulous accelerometers to sense vehicle acceleration in flight. The TNS 1320 is installed at the base of the reentry vehicle and consists of a 26/0 x 21.5 x 16.5 cm box weighing 13.0 kg which contains three digital ring laser gyros (RLGs) and three pendulous integrating gyroscope accelerometers (PIGAs) contained in a shock mounted isolated inertial sensor assembly with associated inertial sensor electronics, a system clock, inertial sensor data processor, and a digital navigation processor. The IMU in each reentry vehicle is activated shortly after first stage ignition and in addition to sensing vehicle acceleration during the terminal maneuvering phase of flight provides measurements of the missile thrust acceleration during boost phase, the deployment impulse imparted to the reentry vehicle during separation from the post boost vehicle, angular acceleration imparted by the reentry vehicle's spin stabilization system, and accelerations imparted to the reentry vehicle during reentry into the atmosphere. For enhanced terminal accuracy the vehicle's inertial guidance system is coupled to a terrain fix system, a terminal guidance system which employs a pair of C band (6.0 to 6.4 GHz) solid-state, frequency modulated continuous wave (FMCW) monopulse radar altimeters blended into the aft body of each reentry vehicle which scan the terrain +/- 5° on each side of the flight path of the reentry vehicle during hypersonic gliding flight towards the target at an altitude of around 30 kilometers following a pull-up maneuver which each vehicle performs after reentering the atmosphere. The returns from the two altimeters are enhanced using doppler beam sharpening to produce a terrain elevation map of the terrain under the flight path of the reentry vehicle which is correlated with a <3 meter resolution digital terrain elevation data (DTED) map generated using interferometric synthetic aperture radar (IFSAR) satellites in order to determine the position and velocity of the reentry vehicle. Low transmit power of the radar altimeters and use of spread-spectrum, frequency modulated continuous waveform (FMCW) operation minimize the risk of reentry vehicle detection by hostile ECM systems.

Warheads:
The RBS 118 missile is designed to contain up to eight multiple independently targetable maneuvering reentry vehicles which are attached to the missile's equipment section. Each maneuvering reentry is 2.0 meters long, 0.58 meters in diameter at the base and consists of a biconic shell with a 10° forward cone and 6° aft cone angle with a launch mass of 275 kg and a 13500 kg/m2 ballistic coefficient with a 2.5 hypersonic lift to drag (L/D) ratio at reentry. Each reentry vehicle contains a thermonuclear warhead, radiation hardened microprocessor based fuzing system, radiation hardened strapdown inertial navigation system and digital guidance computer, terminal fix system, reaction control system, and control actuation system. The vehicle has a graphite-polyimide composite structure with a thermal protection system consisting of a hafnium carbide (HfC) coated tape wrapped 3D carbon phenolic heatshield with a hafnium carbide coated 3D carbon/carbon composite nosecone which is bonded to the underlying composite structure with pyrolytic graphite supports. The vehicle is steered using a split body flap and two yaw flaps constructed from carbon fiber-reinforced silicon carbide (C/SiC) composite actuated using electromechanical actuators powered by a thermal battery onboard the vehicle. The maneuvering reentry vehicles are capable of lateral accelerations of over 100 g at high hypersonic reentry speeds and can perform terminal maneuvers to compensate for boost separation errors, wind shears, and atmospheric conditions that contribute to the miss distance of conventional ballistic reentry vehicles while also providing evasive maneuvers to defeat terminal ballistic missile defense systems. The SG 90 warhead in each reentry vehicle is a two stage thermonuclear warhead with a fusion boosted primary and a fusion second stage with a highly enriched uranium (HEU) tamper which has a designed yield of 500 kilotons, allowing it to crush 70 MPa (10,000 psi) reinforced concrete missile silos and command bunkers within a roughly 200 meter radius. Penetration aids include chaff placed inside the tip of the missile nosecone which is explosively ejected following nose cone separation and 56 inflatable balloons made from aluminum coated mylar which are deployed along with reentry vehicles during the midcourse phase.

Flight Sequence:
Before launch the missile's inertial navigation system is activated and the specified mission trajectory is loaded onto the missile's flight computer. On launch a gas generator inside the missile launch tube is ignited, generating high pressure gas which is fed into a cooling water tank where the water flash vaporizes to steam. The high pressure steam-gas mixture then flows through a nozzle into the missile launch tube and pushes the missile out of the launch tube sufficient force to eject the missile from the submarine from a depth of 50 meters to a height of over 10 meters above the surface. As the missile breaches the surface the gas generator for the first-stage thrust vectoring control (TVC) system ignites to establish nozzle control before the first stage motor is ignited and the aerospike extends to begin the missile's boost phase. The first stage motor burns for approximately 60 seconds until the first stage propellant is exhausted where the second stage TVC system is ignited, the first stage and interstage are ejected, and the second stage is ignited. The second stage burns for another 60 seconds where the nose fairing is ejected, the stage TVC system is ignited, and the second stage is separated from the missile. The third stage is then ignited and burns for 40 seconds. When the third stage has finished burning the post boost control system (PBCS) on the missile's equipment section ignites and the third-stage motor is ejected aft through the center of the equipment section. At this point the stellar-inertial unit on the equipment stage is used to provide a stellar position fix to correct for IMU positional errors that have accumulated during the flight. Following stellar correction the IMU provides transfer alignment to the IMU in each reentry vehicle and the post boost control system is used to maneuver the post boost vehicle to begin dispensing reentry vehicles and inflatable mylar decoys. Following separation from the equipment section the reaction control system in each RV is used to spin up the vehicle and orient it downward for reentry and to reduce its radar cross-section to early warning and ballistic missile defense radars. The RVs then reenter the atmosphere at hypersonic speeds, descending down to an altitude of around 30 kilometers where the vehicle is despun with its reaction control system before performing a 100 g pull-up maneuver to transition into horizontal gliding flight towards the target. During the glide phase the vehicle's terminal fix system is activated and scans the terrain under the flight path of the vehicle, correlating it with a digital terrain elevation map stored in the vehicle's guidance computer which provides a <3 meter accurate terrain fix used to reset the inertial guidance system's accumulated positional errors during hypersonic reentry into the atmosphere. Following the terminal fix system update the vehicle is then programmed to dive towards the target area with a 100 g pull-down maneuver while performing a series a 100+ g weave and corkscrew maneuvers to evade interception by terminal ballistic missile defense systems. The warhead is detonated using radiation hardened microprocessor based intelligent fuzing system with includes a contact fuze and a solid state radar proximity fuze on the underside of the vehicle with radar-updated path length error compensation which triggers warhead detonation when the warhead is within the calculated kill distance of its intended target.

by **The Technocratic Syndicalists** » Mon Oct 23, 2023 9:07 am

RBS 102

General Characteristics:
Type:
Miniature loitering cruise missile

Launch platform:
Aircraft

Guidance:
active LADAR seeker, 2-way RF datalink, GPS/INS
Physical Characteristics:
Weight:
50 kg

Length:
1.6 m

Diameter:
0.18 m

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

Speed:
Mach 0.7/i]

Flight altitude:
[i]1200 - 250 m

Range:
250 km

Endurance:
45 minutes @ 70 km

Overview:
The RBS 102 Wasp is a helicopter launched, long range, autonomous hunter-killer loitering missile designed by SDI Missile Systems. The RBS 102 combines a turbojet powered airframe with a LADAR seeker with automatic target recognition (ATR) and target designation capability, a multi-mode EFP warhead effective against armored and unarmored targets, and a 2-way RF datalink for communication with the launch platform. Following launch from the helicopter the missile flies towards a pre-programmed search area and enters a search pattern and uses its LADAR seeker to search for and detect unknown hostile targets, reporting target types and locations back to the launch platform using it's datalink. Following target detection the missile can either autonomously attack targets or designate them with its LADAR seeker for attack by the launch platform or other assets.

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 missile consists of four sections including the guidance section containing the missile's LADAR seeker, INS/GPS navigation system, software defined radio, thermal battery, and 2-way RF datalink, a warhead section containing the missile's explosively formed penetrator (EFP) warhead, a propulsion section containing a fuel tank and the missile's turbojet motor, and a tail control section containing the missile's tail control surfaces and associated electro-mechanical actuators along with an integral solid-fuel rocket booster used to launch the missile from its launch canister. The Wasp 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 stingle 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. The turbojet gives the missile a maximum speed of mach 0.7 with a designed cruise speed of mach 0.5-0.7 and a loiter speed for maximum endurance of mach 0.3.

Guidance:

Warhead & Fuzing:
The Wasp 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.

SDI Guided Munitions Catalog [DO NOT POST]

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