SDI Air Defense System Catalog [DO NOT POST]

by **The Technocratic Syndicalists** » Mon Jan 29, 2018 9:56 pm

RBS 77 Extended Range Aerospace Defense System

System Overview:
The RBS 77 a rapidly deployable, mobile anti-ballistic missile and anti-hypersonic defense system designed by SDI Missile & Fire Control Systems. The RBS 77 system is designed to protect corps to field army units, military facilities, and civilian infrastructure from medium to intercontinental range ballistic missiles, hypersonic glide vehicles, hypersonic cruise missiles, maneuvering reentry vehicles by intercepting them in their terminal phase with hit-to-kill interceptors. A full RBS 77 ERADS Battery consists of eight TELs with six interceptors each, a trailer mounted X band extended long range acquisition and tracking radar which can track and discriminate incoming missiles and update tracking information for launched interceptors, and a fire control and communications vehicle which controls battery operation and which can communicate with other air defense sensors and systems to allow the RBS 77 system to be seamlessly integrated into a larger integrated air-defense network. The entire RBS 77 system is system is road mobile and can be transported by either ship, rail, or strategics airlifter aircraft in order to allow the entire system to be rapidly deployed around the globe where needed.

Rb 77 interceptor
Weight: 2,000 kg
Length: 7.0 m
Diameter: 0.60 m
Propulsion: Two-stage solid fuel rocket
Operational Range: 1,000 km
Intercept Altitude: 20-500 km
Speed: 5.5 km/s (Mach 18)
Warhead: none- KE hit to kill
Guidance: dual-band infrared FPA
Steering: Thrust-vectoring, solid DACS
Launcher: Trailer based launcher with six canisters

The Rb 77 is a anti-ballistic missile interceptor designed to provide hit-to-kill terminal phase intercept of intercontinental ballistic missile (ICBM) and submarine-launched ballistic missile (SLBM) reentry vehicles, maneuvering reentry vehicles (MaRVs), and hypersonic glide vehicles (HGVs). 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 kilograms, has a specific impulse of 270 seconds, 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 electromechanical actuator (EMA) based gimballed nozzle with +/- 7.5° gimbal angle which is used for first-stage thrust vector control. The second stage weighs 450 kilograms, has a specific impulse of 290 seconds, 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 approximately 75 kg and employs a solid-propellant divert and attitude control system (DACS) for maneuvering. The kill vehicle DACS employs a total of 10 thrusters with variable-area pintle nozzles which allow each thruster to be throttled from 0-100% of maximum thrust for precise in-flight control. 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.

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-atmopsheric 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.

FMG 3300 Extended Range Acquisition and Tracking Radar
Weight: 35,000 kg
Length: 13.0 m
Height: 3.6 m
Frequency: 8.5-10.5 GHz (X-band)
Peak Power: 1.2 MW
Average Power: 180 kW
Instrumented Range: 3,000 km
Tracking Range (1m2 RCS ballistic missile): 2,000 km
Tracking Range (0.01 m² HGV): 600 km
Tracking Accuracy (1m2 RCS ballistic missile): < 5 m range, < 50 µrad angle at 1,000 km
Azimuth: 120°(±60°)
Elevation: 0° - 90°
Target Capacity: 1,000 simultaneous
The FMG 3300 is an advanced X-band AESA radar designed for the RBS 77 system. The FMG 3300 performs long-range search and detection of ballistic missiles and hypersonic weapons, target discrimination to distinguish warheads from decoys and debris, and precision tracking and fire-control-quality state estimation for midcourse guidance of Rb 77 interceptors.The FMG 3300 The radar uses a trailer-mounted, single-faced 9.2 m2 wideband antenna with a total of 81,000 gallium-nitride (GaN) transmit/receive modules with a peak radiated power of approximately 1.2 megawatts and an average power of approximately 180 kilowatts. The FMG 3300’s antenna is a planar, direct-radiating AESA with each radiating element driven by its own dedicated digital transmit/receive channel with independent phase and amplitude control. The radiating aperture is approximately 3.70 meters wide and 2.5 meters tall, with a total illuminated area of approximately 9.25 square meters. The array employs over 81,000 GaN-on-diamond T/R modules arranged as quad-channel tile modules that integrate four T/R channels into a single compact package, allowing finer element spacing. The quad-channel tiles each contain four independent T/R channels sharing a common housing, DC power conditioning, control interface, and thermal baseplate. Each radiating element is a dual-polarized stacked-patch microstrip antenna, fabricated on a multilayer printed-circuit-board (PCB) substrate. Each element has two orthogonal feed ports (horizontal and vertical polarization), both connected to the T/R module, enabling the radar to transmit and receive in any combination of H, V, or simultaneous dual-polarization. The T/R modules are attached to a copper-molybdenum (CuMo) alloy heat spreader, which in turn is pressed against the liquid-cooled cold plate on the antenna’s backplane. This thermal path maintains the GaN junction temperature below 175° C under all operating conditions. The antenna is enclosed in a rigid composite radome that protects the aperture from weather, debris, and handling damage during transport. The radome is a multi-layer sandwich structure comprising an outer skin of woven quartz fabric in a cyanate-ester resin matrix, a syntactic-foam core, and an inner skin of Kevlar fabric in epoxy resin. The quartz outer skin provides low dielectric loss at X-band frequencies (loss tangent less than 0.001), while the Kevlar inner skin provides impact resistance and structural stiffness. The foam core’s thickness is tuned to provide a half-wave impedance match at the center frequency, minimizing reflection loss across the operating band to less than 0.3 dB. The radome’s outer surface is coated with a hydrophobic paint that sheds rain and prevents ice accumulation. For arctic operations, embedded resistive heating elements in the quartz skin can be activated to prevent ice formation, consuming approximately 5 kW of electrical power. The radome is attached to the antenna frame with quick-release latches that allow it to be removed for maintenance access to the subarray panels and T/R modules within approximately 30 minutes.

The FMG 3300 cooling system is a closed-loop liquid cooling system using polyalphaolefin (PAO) synthetic oil as the working fluid. The coolant is pumped at approximately 500 liters per minute through a manifold that distributes it to individual cold plates behind each subarray panel. The cold plates are brazed aluminum structures with micro-channel passages that maximize heat-transfer surface area while minimizing flow resistance. The heated coolant is returned to the trailer-mounted chiller unit, which uses a vapor-compression refrigeration cycle (R-410A refrigerant) to reject the heat to ambient air through a set of fan-cooled condenser coils. The chiller unit has a rated capacity of 400 kW, providing approximately 33 percent margin over the steady-state array heat load of approximately 300 kW at typical duty cycles (the 600 kW figure is the peak heat load at maximum duty cycle, which is sustained only during intense engagement scenarios). The chiller comprises two independent refrigerant circuits, each capable of 200 kW, providing redundancy: if one circuit fails, the radar can continue operating at reduced duty cycle (approximately 50 percent) without exceeding thermal limits. The electronics shelter’s additional 80 kW heat load is managed by a separate forced-air HVAC unit within the shelter, independent of the array cooling system.

The FMG 3300 radar's 1.0 GHz instantaneous bandwidth enables higher range resolution for target discrimination with the radar having the ability to generate high-range-resolution profiles (HRRPs) of detected objects, resolving individual scattering centers along the target’s range axis with a resolution of approximately 15 centimeters, sufficient to distinguish between RVs, heavy decoys, and lightweight balloon decoys based on their range-extent profiles. The radar also measures micro-Doppler signatures which provide additional discrimination cues. In high-PRF track mode, the radar transmits a train of coherent pulses and processes the returns through a Doppler filter bank, implemented as an FFT in the GPU processor. The radar's velocity resolution is approximately 0.015 m/s, enabling the radar to detect and measure micro-Doppler signatures caused by target spin, tumble, nutation, or structural vibration with extreme sensitivity. The onboard radar discrimination capability complements the kill vehicle’s seeker-based discrimination, providing a layered discrimination architecture that improves the probability of directing interceptors at real warheads. For hypersonic targets, the radar’s track-while-scan mode maintains continuous trajectory estimation even as the target maneuvers. The radar's track accuracy (less than 5 meters in range and less than 0.05° in angle at 1,000 km) provides the precision fire-control data needed to support the Rb 77 interceptor’s energy-management guidance law, which requires frequent updates of the target’s position, velocity, and acceleration vector. The radar can track more than 1,000 objects simultaneously, supporting the multi-target environments created by MIRV deployments or coordinated hypersonic salvos. The FMG 3300 processing engine is a cluster of eight ruggedized GPU compute nodes, each containing a high-performance GPU with approximately 50 TFLOPS of single-precision compute throughput, a host processor, high-bandwidth memory (HBM3, approximately 128 GB per node), and high-speed network interfaces. The nodes are interconnected by a low-latency fabric (<400 Gbps per link) that enables data sharing between nodes with microsecond latency. Two nodes are dedicated to digital beamforming and pulse compression, two nodes perform Doppler processing, CFAR detection, and monopulse angle estimation, one node runs the track processor (IMM Kalman filter, track management, state prediction), one node runs the discrimination algorithms (HRRP, ISAR, micro-Doppler, polarimetric analysis, and AI classifier), one node manages the adaptive resource scheduler, waveform generator control, and ECCM algorithms, and one node provides N+1 redundancy (its workload is redistributed across the remaining seven nodes in the event of a node failure). The nodes run a real-time operating system with deterministic scheduling that guarantees the hard-real-time latency requirements of the track and fire-control processing loops. The FMG 3300's ECCM functions includes adaptive digital nulling (ADN) which digitally forms nulls in the receive beampattern on jammer bearings while maintaining main-beam sensitivity, suppressing stand-off and escort jammers without degrading target detection with up to 12 simultaneous nulls, sidelobe blanking (SLB) with auxiliary widebeam antennas thar detects signals received through sidelobes and blanks those returns, rejecting sidelobe jamming and terrain clutter entering through the radar sidelobes, sidelobe cancellation (SLC) that subtracts sidelobe interference from the main beam to eliminate residual sidelobe jamming not fully suppressed by ADN and SLB, pulse-to-pulse and burst-to-burst frequency hopping across the full 2.0 GHz tunable bandwidth to defeats spot-frequency jammers, pseudo-random pulse compression code changing on a pulse-to-pulse basis with multiple simultaneous waveforms on different frequencies to defeat DRFM jamming, adaptive power management with transmit power scaled dynamically per beam position based on threat and jamming environment that can concentrates power on jammed sectors while reducing emissions in unjammed sectors, and AI-driven real-time assessment of the electromagnetic environment with automatic ECCM mode selection and parameter optimization to adapts to evolving jamming threats without operator intervention.

The FMG 3300 radar system elements include the phased array antenna, the electronic equipment unit, a 1.5 MW prime power unit, a cooling equipment unit which provides cooling for the antenna array, and an operator control unit which contains operator consoles for operations, maintenance and communications monitoring. The FMG 3300 is transported in two T 44 loads. The first load carries the antenna unit and its turntable pedestal on a specialized semi-trailer. The second load carries the electronics shelter (containing the radar processor, signal generator, waveform controller, and operator interface), the 1.5 MW diesel generator set, and the liquid cooling system’s chiller unit, each on separate trailers towed by HTTS prime movers. At the emplacement site, the antenna trailer is positioned and leveled, the antenna is erected from its horizontal transport position to its near-vertical operating position using integral hydraulic actuators, and cables are connected to the electronics shelter and generator. The entire radar emplacement process takes approximately 45 minutes from arrival to first radiation, with an additional 15 minutes for automated self-test and boresight calibration. Teardown is accomplished in approximately 30 minutes.

by **The Technocratic Syndicalists** » Thu Mar 08, 2018 10:12 pm

RBS 73 Hypersonic Defense Intercept System

System Overview:
RBS 73 Hypersonic Defense Intercept System (HYDIS) is a fully road-mobile missile defense and area defense SAM system developed by SDI Missiles & Fire Control systems. Designed to complement the RBS 77 ERADS system as the middle tier of SDI designed air defense systems the RBS 73 HYDIS is designed to intercept tactical and medium range ballistic missiles, maneuvering hypersonic glide vehicles and hypersonic cruise missiles, and conventional aerial targets including cruise missiles and manned and unmanned aircraft at all altitudes. Designed from the onset to provide air defense cover for both fixed sites and for corps and above level formations the FABMIS system is highly mobile with all battery elements mounted on SDI 10x10 Heavy Tactical Truck System (HTTS) chassis. An individual RBS 73 battery consists of eight TELs, an FMG 900 UHF band Surveillance Radar, two FMG 600 X band Multifunction Fire Control Radars (MFCRs), and a FABMIS Tactical Operations Center (TOC). Four to six RBS 73 batteries are organized into a battalion which includes a headquarters and headquarters battery with command and control, communications, and maintenance units including reloading, power, and repair parts transporters. The RBS 73 Battle Management Command, Control, Communications, Computers and Intelligence (BMC4I) system manages all FABMIS battery elements and integrates the RBS 73 system with other air defense elements, AEW, space-based sensors, and other tactical and strategic assets.

Rb 73 interceptor
Weight:
1,500 kg

Length:
6.5 m

Diameter:
25 cm interceptor, 50 cm booster

Warhead:
15 kg lethality enhancer

Propulsion:
Solid fuel rocket

Operational range :
3-300 km

Flight ceiling:
0-40 km

Speed:
Mach 7.5 (2,250 m/s)

Guidance system:
Active radar, imaging infrared homing

Launcher:
Trailer based launcher with six canisters
The Rb 73 interceptor is a two stage, solid fuel rocket powered interceptor designed to defeat the full spectrum of air and missile threats. The interceptor is specifically optimized for the demanding kinematics of the counter-hypersonic mission, where closing velocities can exceed 5 km/s and engagement timelines are compressed to tens of seconds. The missile is powered by a solid fuel booster and a a dual pulse solid fuel upper stage motor which provides high acceleration and endgame divert and maneuverability capability to intercept maneuvering ballistic missile reentry vehicles and other high speed maneuvering threats. Midcourse guidance is provided by an internal navigation system and command guidance using the battery's multi-function fire control radar. Terminal homing is provided by a dual millimeter wave (MMW) active radar and imaging infrared seeker which provides highly accurate tracking of high speed, low RCS targets in all weather conditions. The interceptor engagement envelope covers the full range of air and missile defense missions. Against manned and unmanned fixed-wing aircraft and cruise missiles at ranges from 3 km to 300 km and altitudes from 0 m to 40 km. The interceptor's high speed provides a large no-escape zone against maneuvering aircraft, and the dual-mode seeker ensures engagement capability in all weather conditions including heavy ECM. Against short- and medium-range ballistic missiles (up to 3,000 km class) during their terminal and upper-terminal descent phase, at engagement altitudes from 5 km to over 30 km. The hit-to-kill mechanism provides high lethality against separating warheads including those potentially carrying WMD payloads. Against maneuvering hypersonic glide vehicles and hypersonic cruise missiles the KV's high lateral acceleration capability and dual-mode seeker provide intercept capability. The missile is housed in a sealed annular composite canister measuring approximately 6.5 m in length and 0.65 m in diameter, compatible with the TEL vertical launch system. The canister provides environmental protection, maintenance free storage life exceeding 15 years, and serves as the launch tube.

FMG 600 X-band Multifunction Fire Control Radar
Weight:
20,000 kg

Frequency:
10-12 GHz (X band)

Peak Power:
150 kW

Average Power:
30 kW
Antenna Technology:
Active Full Phased Array, GaN Tx/Rx modules

Antenna Aperture:
20 m2

Antenna Rotation Rate
30 RPM
Tracking Range (Air Breathing Target):
280 km

Azimuth:
360°

Elevation:
-10°to +90°

Target Capability:
500+ simultaneous
The FMG 600 is a multifunction search and fire control radar is an X band (10 to 12 GHz) 3D solid state digital AESA radar which provides precision target tracking and classification capabilities and surveillance capability independent of the longer ranged FMG 900 search radar. The FMG 600 employs a solid-state, fully digital Active Electronically Scanned Array operating in the X-band. The antenna is a square aperture approximately 3.6 m per side housing over 12,000 full duplex GaN T/R modules in a densely packed lattice with approximately 15 mm inter-element spacing. Each T/R module incorporates a full radar transmit/receive chain with GaN power amplifier, GaN low-noise amplifier, digital phase and amplitude control, and high-speed ADC for element level digitization. The 3.6 m aperture at X-band yields a pencil beam of approximately 0.18° in both azimuth and elevation providing angular resolution fine enough to resolve closely spaced objects such as ballistic missile warheads, decoys, and debris within a threat cloud and to achieve precision monopulse angle tracking with errors well below 0.01°. The FMG 600 radar can be rotated 360° and is designed for sector surveillance with +/- 60° electronic beam scanning capability in both azimuth and elevation and the ability to track targets from -10° to +90° in elevation.The antenna is mounted on a high-speed rotary pedestal with continuous 360° rotation capability at rates up to 30 RPM. During rotation the AESA electronically scans its beams within the instantaneous ±60° sector, interleaving search, track, and fire control functions on a pulse-to-pulse basis under timeline-based resource management. The FMG 600 further uses its main beam for uplink and downlink missile communications through a pair of X band transceiver antennas on the Rb 73 interceptor airframe which provides midcourse command guidance capability for the interceptor. An IFF antenna and subsystem is also integrated into the antenna to support threat identification and classification.

While the FMG 900 provides the primary wide-area surveillance picture the FMG 600 MFCR independently performs complementary surveillance functions that enhance the system's overall detection capability. Upon receiving a detection cue from the FMG 900 or an external sensor the MFCR can perform a focused confirmation search in the designated sector, exploiting its higher angular and range resolution to confirm, refine, and classify the detected target. The MFCR's X-band resolution often resolves individual objects within a target group that appears as a single return on the UHF SR. The MFCR maintains its own independent search fence, typically covering the full 360° volume from surface to 90° elevation to detect threats that may have been missed by the SR or that approach from unexpected directions, providing defense-in-depth at the sensor level. The FMG 600 MFCR's high range resolution (<0.15 m in wideband mode) and high Doppler resolution enable extraction of jet engine modulation signatures, high-range-resolution profiles (HRRPs), and inverse synthetic aperture radar (ISAR) imagery for automatic target recognition (ATR). These non-cooperative target identification techniques allow the system to classify targets by type and even by specific aircraft model without relying on IFF transponder responses. Against ballistic missile threats, the MFCR can resolve and individually track the warhead, spent booster stages, decoys, chaff, and debris fragments within a threat complex, supporting lethal object discrimination for efficient interceptor allocation. During engagements the FMG 600 provides fire control data and interceptor support throughout the kill chain. The MFCR provides track updates at rates up to 10 Hz per target in fire control mode, with position accuracy better than 5 m in range and 3 m cross-range at 300 km, and velocity accuracy better than 0.5 m/s, this data driving the interceptor's midcourse guidance commands. The MFCR transmits encrypted midcourse guidance correction commands to the interceptor via a dedicated X-band TT&C (telemetry, tracking, and command) link with the large aperture and high EIRP of the AESA providing reliable uplink communication at ranges up to 300 km in EW heavy environments. Post intercept the MFCR performs kill assessment by tracking the target through the intercept point, detecting changes in the target's radar signature (fragmentation, velocity change, RCS fluctuation) that indicate a successful engagement, and automatically recommending re-engagement if kill assessment is negative. The digital beamforming architecture allows the MFCR to simultaneously support fire control operations against up to 80 targets, interleaving precision track updates and guidance uplinks across all active engagements within the radar's timeline.

The 1 GHz instantaneous bandwidth of the radar provides exceptional frequency agility, with pulse-to-pulse frequency hopping across 1,000 discrete frequency channels, forcing a threat jammer to either spread its power across the full 1 GHz band, reducing effective jamming spectral density by 30 dB compared to a narrowband jammer, or accept that the majority of its jamming pulses will miss the radar's operating frequency. The 12,288-element digital array provides over 12,000 spatial degrees of freedom for adaptive interference suppression. In operational scenarios with 10 to 20 simultaneous jammer sources the system retains sufficient degrees of freedom to simultaneously null all jammers while maintaining full target detection and tracking capability. The dense element spacing and large element count enable extremely low sidelobes (−35 dB or below in standard mode, −55 dB in ultra-low sidelobe mode with amplitude tapering) making the radar highly resistant to sidelobe jamming even from high power dedicated escort jammers. The MFCR can operate in a spread-spectrum mode using noise-like waveforms with very high time-bandwidth products (up to 10⁶), distributing its energy below the noise floor of hostile ESM and radar warning receivers. In this mode, the radar is effectively undetectable at ranges beyond 50 to 100 km while maintaining useful detection capability through coherent integration of the spread-spectrum returns. To counter anti-radiation missiles (ARMs), the MFCR employs emission control (EMCON) management with rapid on/off cycling, power management to reduce detectable emissions below ARM seeker sensitivity thresholds, and frequency agility to prevent ARM seekers from acquiring stable lock. The system can also coordinate with passive decoy emitters to seduce incoming ARMs away from the actual radar position. An AI-driven electronic warfare management subsystem continuously monitors the electromagnetic environment through the radar's own receivers and inputs from dedicated ESM systems, classifying detected emitters and jamming signals and automatically selecting optimal combinations of ECCM techniques in real time without operator intervention. This autonomous EP response operates at machine speed, countering fast-switching jamming

FMG 900 UHF-band Surveillance Radar
Weight:
30,000 kg

Frequency:
400-450 MHz (UHF band)

Peak Power:
46 kW

Average Power:
12 kW
Antenna Technology:
Active Full Phased Array, GaN Tx/Rx modules

Antenna Aperture:
50 m2

Antenna Rotation Rate
6 RPM
Instrumented Rang:
1,500 km

Tracking Range (5 m² Air-Breathing Target):
1,000 km

Azimuth:
360°

Elevation:
-10°to +90°

Target Capability:
1,000+ simultaneous
The FMG 900 is a UHF band (420 to 450 MHz) 3D solid state digital AESA radar that provides extended range a 360° threat detection against maneuverable low signature threats including short and medium-range ballistic missiles, cruise missiles, and other air-breathing targets. The radar employs a solid-state, fully digital Active Electronically Scanned Array (AESA) antenna operating in the UHF band (400 to 450 MHz). The antenna assembly consists of a large rectangular planar array measuring approximately 6.4 m wide by 9.6 meters tall in its deployed configuration housing over 3,000 individual Gallium Nitride (GaN) transmit/receive (T/R) modules. Each T/R module constitutes a fully independent radar channel with its own high-power GaN-on-SiC amplifier (peak power output of approximately 100 W per element), low-noise GaN receive amplifier, phase shifter, amplitude controller, built-in test circuitry, and high-speed analog-to-digital converter (ADC). The element-level digitization means every element functions as an independent radar receiver with all beamforming, beam steering, and adaptive processing performed digitally in the back-end signal processing subsystem. The radar can be mechanically scanned 360° in azimuth and electronically scanned +/- 60° in azimuth and elevation and can either be operated in a 6 RPM 360° mode with a 1,000 km instrumented range or a sector surveillance mode with a 1,500 kilometer instructed range. Elevation coverage is up to 40° in search mode and up to 90° in track mode with the radar having the ability to operate simultaneously in long range search (0 to 40° coverage), valley coverage (0 to -10°coverage), and target track modes (-10°to +90° coverage). The antenna is mounted on a heavy-duty hydraulic erection mast and rotary pedestal atop the HTTS 10x10 chassis. In transit configuration the array folds into a compact stowed profile within the vehicle's height and width envelopes for road transport and strategic lift. Upon arrival at a firing position the array is hydraulically erected and locked and the rotary pedestal begins continuous 360° rotation. During rotation, the AESA electronically steers its beams within the instantaneous ±60-degree forward sector, providing continuous volumetric search coverage as the antenna rotates. The system can also operate in sectors can mode, halting rotation to concentrate radar energy and processing capacity on a specific threat axis.

The FMG 900's fully digital architecture enables a high level of waveform agility and signal processing sophistication. Unlike analog beamforming radars where the transmitted waveform and receive beam pattern are fixed per pulse repetition interval, the FMG 900''s element-level digital control allows simultaneous formation of multiple independent receive beams from a single transmitted pulse, real time optimization of transmit waveform parameters on a pulse-by-pulse basis, and coherent combination of element-level data with arbitrary weighting functions. The signal processing subsystem can forms up to 64 simultaneous independent receive beams from the 3,072 digitized element channels in real time, providing instantaneous volumetric coverage within the antenna's electronic scan envelope. The waveform generator a direct digital synthesis (DDS) system capable of generating arbitrary waveforms including linear FM chirp, nonlinear FM, phase-coded, frequency-hopped, and hybrid waveforms. Pulse widths are variable from 1 μs to 2 ms, with instantaneous bandwidth up to 50 MHz. A matched filter and adaptive mismatch filter processing pulse compression engine providing pulse compression ratios up to 60,000:1, enabling long range detection with fine range resolution, approximately 5 m with full 50 MHz bandwidth. Doppler processing consists of coherent integration across up to 512 pulses per coherent processing interval (CPI), with adaptive clutter cancellation using space-time adaptive processing (STAP) algorithms applied across the digital element channels. Multi-dimensional Constant False Alarm Rate (CFAR) algorithms operate across range, Doppler, azimuth, and elevation dimensions, with adaptive threshold selection for operation in dense clutter and jamming environments. Track processing is through multiple hypothesis tracking (MHT) algorithms maintaining up to 1,500 simultaneous surveillance tracks, with automatic track initiation, confirmation, coast, and deletion. Ballistic missile tracks are automatically identified through trajectory analysis and flagged for priority processing. The waveform scheduling system operates on a timeline based resource management architecture. Each rotation of the antenna is divided into thousands of individual dwell slots, and an artificial intelligence (AI) assisted scheduling algorithm dynamically allocates these dwells across competing tasks including horizon search, elevated search, track update, threat confirmation, track while scan based on the current tactical situation, sensor tasking commands from the TOC, and the radar's own assessment of the threat environment. This approach ensures that the radar continuously adapts its search and track behavior to optimize detection probability against the current threats while maintaining broad area surveillance.

The FMG 900 incorporates multiple ECCM techniques designed to ensure continued effective radar operation in severe electronic warfare environments. By independently weighting the amplitude and phase of each of the 3,072 element channels in the digital beamformer, the system can instantaneously place deep adaptive nulls on the bearing of detected jammers while maintaining the main beam's gain and sidelobe integrity. Unlike analog null steering which is limited to a small number of degrees of freedom, the digital architecture can simultaneously null dozens of independent jammer sources across the entire spatial hemisphere. Dedicated auxiliary antenna elements with broad patterns are used as sidelobe blanking channels, automatically gating out any pulse received with greater energy in the auxiliary channel than in the main beam. Additionally, generalized sidelobe canceller (GSC) algorithms subtract weighted auxiliary channel signals from the main channel to suppress spatially distributed sidelobe interference. The 50 MHz instantaneous bandwidth of the GaN T/R modules, combined with DDS waveform generation, enables pulse-to-pulse frequency agility across the entire 400 to 450 MHz operating band, with inter-pulse frequency changes executed in under 10 microseconds. This frequency hopping prevents a jammer from concentrating its energy on the radar's operating frequency and forces the adversary to spread jamming power across the entire band, reducing effective jamming power spectral density by 15 to 25 dB. The radar continuously varies its pulse width, modulation type, and coding scheme on a pulse-to-pulse or CPI-to-CPI basis under algorithmic control, preventing the adversary's electronic support measures (ESM) from characterizing and matched-filtering the radar's emissions for effective DRFM-based deception jamming. For operations requiring electromagnetic signature reduction the FMG 900 can operate in spread-spectrum LPI modes using wide time-bandwidth product waveforms at reduced peak power, distributing radar energy below the detection threshold of hostile ESM receivers while maintaining detection capability through coherent integration gain. In LPI mode, detection range is reduced but the radar becomes effectively invisible to threat warning receivers at ranges beyond 200 to 300 km. The digital beamformer applies Taylor and Chebyshev amplitude weightings across the aperture to achieve low sidelobe levels (<−30 dB first sidelobe in standard mode, <−45 dB in ultra-low sidelobe mode) reducing the radar's vulnerability to sidelobe jamming. The radar's precision angle-of-arrival estimation (interferometric processing across the large aperture) enables passive tracking of jammer emitters with sufficient angular accuracy to support HOJ engagement cueing to the fire control system. Advanced coherence analysis algorithms further detect inconsistencies in range-Doppler-angle characteristics of returns to identify and flag Digital Radio Frequency Memory (DRFM) repeater jamming, enabling automatic classification of deceptive returns and their removal from the track picture.

by **The Technocratic Syndicalists** » Thu Nov 05, 2020 1:19 pm

RBS 81

System Overview:
The RBS 81 is a mobile short to medium range air defense which is intended to provide all-weather detection and defeat of fixed wing and rotary aircraft, cruise missiles, and precision guided and loitering munitions for division and corps level formations. The RBS 81 system consists of three main components including the Rb 81 missiles and transporter erector launchers, FMG 200 surveillance radar, and a tactical operations center (TOC) which acts as the command and control unit of the RBS 81 system. All RBS 81 components are mounted on SDI HTTS 8x8 carriers which give the system excellent on-road and cross country mobility for supporting armored and mechanized units.

An RBS 81 battery consists of a headquarters section with a tactical operations center (TOC), a radar section with two FMG 200 surveillance radars, and two firing platoons with eight Rb 81 missile TELs each. The TOC acts as the battlespace management and command and control node of the battery and is responsible for sensor control, datalink management, integrated air picture generation, target track identification and classification, weapon and engagement control, and kill assessment functions. Targets to be engaged can be passed to the FDC from the RBS 81 battery's own surveillance and fire control radars, from radars of neighboring batteries, or from other radars and sensors including aircraft or surface vessels. The TOC is contained in an ISO container sized shelter mounted to an HTTS 8x8 chassis and contains two crew stations for a tactical control officer (TCO) and tactical control assistant (TCA). The TOC can be located up to 25 kilometers from the fire units and surveillance radars when using radio datalink communications or up to 15 kilometers when using fiber optic cables.

The surveillance section of the RBS 81 battery consists of two SDI FMG 200 air surveillance radars with integrated IFF antennas mounted to HTTS 8x8 vehicles. The FMG 200 is used to provide long range target detection and tracking and target handoff to the individual fire units for target engagement. Each fire unit consists of a TEL (transporter erector launcher) vehicle built on a HTTS 8x8 chassis which mounts a short range electro-optical surveillance sensor and a launcher with twelve Rb 81 missiles ready to fire in sealed blast and fragment hardened launch canisters. Reloading of each TEL can be accomplished in several minutes either using a flat-rack and cargo hook system to replace the entire launcher or using a crane to replace individual individual launch canisters.

FMG 200 Surveillance Radar
Frequency:
5.2-5.9 GHz (C band)

Antenna technology:
Active Phased Array, GaN Tx/Rx modules

Antenna rotation rate:
30 or 60 RPM

Instrumented range:
400 km

Ceiling:
30 km

Azimuth:
360°

Elevation:
0° to +90°

Target RCS
< 0.01 m²

Target Capability:
1,000 simultaneous
The SDI FMG 200 is the combined surveillance and fire control sensor of the RBS 81 system. The FMG 200 is an advanced C band (5.2-5.9 GHz), GaN solid state 4D Active Electronically Scanned Array (AESA) radar system employing a single rotating antenna face with element-level digital beamforming. The radar provides simultaneous air surveillance, ballistic missile defense (BMD), fire control, missile guidance uplink, counter-rocket/artillery/mortar (C-RAM), weapon location, and non-cooperative target recognition (NCTR) capabilities through software-defined, dynamically managed radar resource allocation. The FMG 200 features an instrumented range of 450 km with the ability to track a 1 m² RCS fighter size target at 250 km and a 0.01 m² low-RCS cruise missile at 80 km, 360°azimuth coverage through 60 RPM mechanical rotation combined with ±60° electronic beam steering in azimuth and 0–90° in elevation, tracking of more than 1,000 simultaneous targets with 100 fire-control-quality updates at up to 10 Hz in staring mode, detection and tracking of targets with radar cross-sections below 0.01 m², autonomous ballistic missile detection and tracking, and a deployment time of less than 15 minutes by a two-person crew. The radar features <0.2° azimuth, <0.3° elevation, and <15 meter range accuracy and provides target detection and identification, cued search and track, own weapon tracking, and kill indication functions to the RBS 81 system. The radar additionally features a cued search function which scans a dedicated sector twice per mechanical rotation, the ability to initiator a target a track within a single scan, and automatically classifies specified targets and allocates additional cued tracks to specified high priority targets, and an ELSS (enhanced low, slow and small) surveillance mode which is optimized for detecting and tracking small UAVs and loitering munitions in high clutter environments. The entire radar system including antenna assembly, rotating pedestal, electronics shelter, prime power, and cooling—is integrated into a single standard ISO container size module r with a gross weight of less than 12 metric tons, enabling transport by any platform capable of handling a standard intermodal containers.

The FMG 200’s signal processing architecture is built around a high-performance embedded computing (HPEC) chassis delivering 500+ TFLOPS of heterogeneous compute throughput, combining multi-core CPUs, GPUs, and FPGAs. The processing system executes the following functions simultaneously including continuous 360° search from surface level to 90° elevation with adaptive dwell scheduling that allocates additional radar time to sectors of interest based on threat cueing, terrain masking analysis, and historical threat approach corridors, tracking of up to 1,000 simultaneous tracks in track-while-scan mode with 100 tracks maintained in dedicated fire-control quality with update rates of 10 Hz or better, AI/ML-based automatic target classification engine fusing C-band RCS measurements and kinematic behavior analysis to classify targets into 25+ threat categories with confidence scoring, C-band datalink uplink to Rb 81 missiles in flight, providing mid-course guidance corrections and target updates, and implementation of real-time adaptive electronic counter-countermeasure algorithms including wideband frequency agility, sidelobe blanking and cancellation, adaptive null steering against jammers, and cognitive radar techniques that autonomously modify waveforms based on the detected electronic warfare environment.

The FMG 200 radar is mounted on a dedicated SDI HTTS 41.815 8x8 chassis with an integrated 150 kW diesel generator set, liquid cooling system, and leveling jacks. The radar antenna assembly is mounted on a telescoping mast that raises the array phase center to 8 meters above ground level during operation, maximizing low-altitude coverage and reducing terrain masking effects. The mast can be lowered to transport height in less than 3 minutes for displacement. The radar vehicle includes a two-person radar operator cab at the rear of the chassis housing system monitoring displays, maintenance diagnostics, and a backup fire control interface for degraded operations when communications with the TOC are lost. The vehicle’s electronic architecture is designed for single-operator operation during normal networked operations, with the radar functions fully automated and managed remotely from the TOC.

Rb 81 Interceptor
Weight: 300 kg
Length: 5.0 m
Diameter: 280 mm
Propulsion: Dual-pulse solid fuel rocket
Operational Range: 1-120 km
Intercept Altitude: 0-30 km
Speed: Mach 4.0
Warhead: 25 kg blast/fragmentation
Guidance: Active radar homing (ARH)
Steering: Thrust-vectoring, control fins
Launcher: Trailer based launcher with twelve canisters
The Rb 81 interceptor used with the RBS 81 system is designed to intercept aircraft, cruise missiles, and short range ballistic missiles and combines advanced dual-mode guidance (mid-course datalink with terminal active radar and imaging infrared seekers), a high-energy dual-pulse rocket motor, extreme maneuverability, and a multi-mode warhead to provide engagement capability against the complete spectrum of aerial threats from low-altitude Group 1 UAS to terminal-phase tactical ballistic missile warheads. The missiles has a maximum intercept range of 120 kilometers and can engage targets traveling at altitudes up to 30 kilometers.

Following canister ejection and booster ignition, the missile executes a rapid post-launch turn-to-bearing maneuver using thrust vector control (TVC) vanes in the booster exhaust, aligning the missile with the initial intercept heading provided by the fire control system. During this phase, the missile is guided by its onboard strapdown inertial navigation system using a fiber-optic gyroscope inertial measurement unit (IMU) and receives course correction commands via the C-band datalink from the FMG 200 radar. During the mid-course phase, the missile flies on INS with continuous updates from the FMG 200 radar’s C-band uplink. The radar provides the missile with refined target position, velocity, and acceleration estimates derived from the radar’s own tracking, enabling the missile’s onboard guidance computer to generate an optimized intercept trajectory using proportional navigation guidance with predicted intercept point lead. The datalink is two-way: the missile transmits its own position, velocity, and health status back to the fire control system, enabling the TOC to assess missile flyout status and reallocate targets if necessary. The mid-course datalink can simultaneously support up to 128 missiles in flight across all battery TELs, with each missile receiving unique guidance updates at a rate of 5 Hz. This capacity enables the RBS 81 battery to conduct large-scale salvo engagements against mass raid scenarios without datalink saturation.

At a range of approximately 15 to 20 km from the predicted intercept point (or closer for short-range engagements), the missile activates its dual-mode terminal seeker consisting of a Ku-band active radar homing (ARH) seeker and a long-wave infrared (LWIR) imaging infrared (IIR) seeker. The Ku-band ARH seeker provides autonomous target acquisition and tracking in all weather conditions, day or night, with a detection range of 20+ km against fighter-sized targets. The seeker employs a monopulse antenna with electronic scanning capability and advanced signal processing for home-on-jam (HOJ) capability, enabling engagement of actively jamming targets. The Ku-band frequency provides narrow beamwidth and excellent angular resolution for distinguishing closely spaced targets, decoys, and countermeasures. Imaging Infrared: The uncooled LWIR IIR seeker provides a passive, unjammable terminal guidance mode with high angular resolution. The 640×512 pixel vanadium oxide (VOx) microbolometer focal plane array generates thermal imagery that the onboard image processor matches against an embedded target library using AI-based automatic target recognition (ATR) algorithms. The IIR seeker enables engagement of targets that employ effective radar countermeasures, including low-RCS stealth aircraft, chaff corridors, and active jamming that degrades the ARH seeker. The missile’s onboard guidance computer fuses data from both seekers in real time, selecting the optimal guidance mode or combining both inputs in a weighted Kalman filter to maximize terminal accuracy. In the fused mode, the missile is designed to achieve terminal miss distances consistently below 1.5 meters against maneuvering targets, and below 0.5 meters against non-maneuvering targets, well within the warhead’s lethal radius.

RBS 81 TEL
The RBS 81 TEL is a highly mobile, twelve-round Transporter Erector Launcher designed to receive target data and engagement commands and execute autonomous or directed missile launches against assigned targets. Each TEL is a self-contained fire unit capable of independent operations with a mast-mounted passive EO/IR sensor for autonomous backup engagements or when receiving cueing from external sources. The TEL is mounted on a SDI HTTS 41.815 8x8 chassis, providing excellent cross-country mobility, high payload capacity, and commonality with existing logistics and automotive supply chains. The launcher assembly occupies a flatrack compatible pallet interface, allowing integration onto alternative vehicle platforms or fixed-site installations.

The launcher assembly consists of a single removable 12-pack launcher module with twelve Rb 81 missiles in individual sealed canister-launchers arranged in a 6-wide by 2-high configuration. The launcher module uses a hydraulic erection frame that raises the module from the horizontal travel position to a fixed 90-degree launch angle. The fixed launch angle eliminates the need for complex, heavy, and maintenance-intensive precision azimuth and elevation drive mechanisms, the missile’s onboard guidance system performs a post-launch turn-to-bearing maneuver to align with the target intercept geometry as commanded by the fire control system. Each launcher module weighs approximately 7,200 kg fully loaded and is handled as a single unit during reload operations. Empty modules are removed from the TEL using a standard HMTT-LHS (Load Handling System) compatible flat-rack interface, and pre-loaded modules are installed in their place. This modular reload concept enables a trained crew to reload all twelve missiles in less than 10 minutes including crane positioning, module extraction, replacement, and connector verification. The rectangular canister-launchers serve as the missile’s shipping container, storage container, and launch tube throughout the weapon’s 15-year service life. No field-level handling of the missile outside its canister is ever required. Each canister includes an embedded health monitoring system that continuously reports missile status (propellant integrity, seeker operability, battery charge state, environmental exposure history) through the TEL’s fire control interface.

Each TEL is equipped with an onboard mission computer that receives target data and engagement commands from the BMS network via an encrypted C-band directional datalink and Link 16 as a backup. The mission computer manages missile initialization, pre-launch Built-In Test (BIT), launch sequencing, and post-launch datalink relay to missiles in flight. The TEL can execute launches in fully remote mode (commanded by the TOC with no crew present at the TEL) or in local mode (initiated by the TEL commander using the cab-mounted fire control display). The TEL also carries a lightweight mast-mounted passive EO/IR sensor consisting of a mid-wave infrared (MWIR) camera and a day television camera on a 6-meter telescoping mast, providing the TEL with organic target acquisition and tracking capability for autonomous backup engagements when the primary radar link is unavailable. This sensor provides detection of fighter-sized targets at ranges exceeding 25 km in clear conditions.

by **The Technocratic Syndicalists** » Thu Dec 17, 2020 6:22 pm

Manticore C-RAM

System Overview
Weight: 26,000 kg
Length: 19.8 m
Width: 3.7 m
Height: 4.3 m
Crew: 4
Rate of Fire: 8,000 RPM
Range: 3,000 m self destruct

by **The Technocratic Syndicalists** » Wed Aug 10, 2022 10:34 am

RBS 82 Anti-Satellite (ASAT) System

System Overview:
The RBS 82 is a rapidly deployable, highly mobile anti-satellite system designed to intercept and destroy satellites and spacecraft in low earth orbit. The RBS 82 system consists of two primary elements; the Rb 82 missile subsystem consisting of the Rb 82 interceptor and erector launcher (TEL) trailer and the weapon control system consisting of Battalion Control Element (BCE) and Battery Command Center (BCC), and which which interfaces with an ASAT BMC3 (battle management command, control and communications system. A complete RBS 82 battalion system consists of a battalion headquarters with a Battalion Control Element (BCE) and three firing batteries each with four erector launchers and a Battery Command Post (BCP). The entire RBS 82 ERADS is system is road mobile and can be transported by either ship, rail, or strategic airlifter aircraft in order to allow the entire system to be rapidly deployed around the globe where needed.

Rb 82 interceptor
Weight: 10,400 kg
Length: 12.0 m
Diameter: 1.0 m
Propulsion: Three-stage solid fuel rocket
Operational range: 5,000 km
Intercept altitude: 100 - 3,000 km
Speed: 8.0 km/s
Warhead: none- KE hit to kill
Guidance: dual-band infrared FPA
Steering: Thrust-vectoring, bipropellant DACS
Launcher: Trailer based launcher with two canisters

The Rb 82 interceptor is a direct ascent anti-satellite interceptor which is capable of reaching all satellite and spacecraft targets in low earth orbit. The components of the Rb 82 include a multi stage solid fuel rocket booster 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 booster consists of three solid fuel rocket stages including a triple pulse kick stage which accelerates the kill vehicle to a maximum burnout velocity of 8.0 km/s. The kill vehicle consists of the seeker, GN&C, downlink communications, airborne power, propulsion system, and kill enhancement device (KED) sections and autonomously homes in on and and destroys targeted satellites via kinetic impact.

The missile with its launch canister is transported and launched from a trailer based erector launcher (EL) which is towed by an SDI HTTS 10X10 vehicle. The EL includes an elevating assembly with mounts for two sealed missile launch canisters along with a ground integrated electronic unit (GIEU), a hydraulic control panel, and two 28-volt DC power supply systems. The GIEU ground integrated electronic units includes built-in test (BIT) functions and missile status monitoring capability and provides launch site communications between the transporter erector-launcher and the battery command center.

Battalion Control Element
The Battalion Control Element (BCE) acts as the command post for the RBS 82 battalion and is responsible for readiness checks, planning and executing intercept solutions, interfacing with ASAT BMC3 systems to receive, process and warning, alerts, and firing orders, interfacing with the battery command posts to relay firing orders and weapon data loads, and interfacing with SATCOM to receive in flight missile and kill vehicle status via satellite relay downlink for real-time intercept monitoring and kill assessment. The BCE is contained in a 6.0 meter ISO container sized shelter with air conditioning and NBC filtration and contains three dual screen display operator consoles and is mounted to an SDI HTTS 8x8 Heavy Tactical Truck System chassis.

Battery Command Posy
The Battery Command Post acts as the command post for individual RBS 82 batteries and interfaces with the Battalion Control Element to receive firing orders and weapon data loads, transmits missile data loads to individual Rb 82 interceptors, sends missile launch signals to erector-launcher units, performs post-launch up-link management of interceptors, monitors the pre-launch health status of individual missiles and erector-launchers, and coordination with other BCPs deployed in the RBS 82 battalion. Like the BCE the BCP is contained in a 6.0 meter ISO container sized shelter with air conditioning and NBC filtration and contains three dual screen display operator consoles and is mounted to an SDI HTTS 8x8 Heavy Tactical Truck System chassis.

by **The Technocratic Syndicalists** » Fri Oct 04, 2024 8:36 pm

RBS 85 Manticore

System Overview:
The RBS 85 Manticore is a mobile, all-weather short range air defense system designed by SDI Missiles & Fire Control systems. The RBS 85 system consists of a modular, electrically driven 360° traversable turret which is fitted with a 360° surveillance radar, a multispectral electro-optical tracking sensor system with forward looking infra-red (FLIR) and TV trackers, a laser rangefinder, and a carbon dioxide (CO2) missile guidance system, and eight ready to fire missiles contained in two four missile launcher-containers carried on either side of the turret. Two control consoles, one for the radar operator and the other for the gunner/electro-optics operator are placed inside the carrier vehicle. The entire system is controlled using a digital microprocessor based turret and control assembly consisting of a control and guidance computer which optimizes missies guidance laws and manages the various fire unit operating modes, a coordination computer which manages the fire unit tasks, allows data input required for air defense coordination function (data exchanges between fire units and other external defense sensors or systems concerning the local air situation) and monitors the availability of the fire unit through a built-in-test (BIT) system, and both gunner and commander operations and fire unit control panels with digital multi-function displays which are used to manage the surveillance, tracking and firing modes of the fire unit as well as supporting the system status functions. The target engagement cycle from detection to interception is entirely automatic with the gunner only pressing buttons twice to confirm lack of target IFF response to reduce the risk of targeting friendly aircraft.

The entire turret with its associated control consoles and hardware can be mounted to all types of tracked and wheeled vehicles and is intended to provide front-line battalion or brigade level mobile air defense or permanent or semi-permanent site defense against air threats such as fixed-wing aircraft, attack helicopters, cruise missiles, tactical missiles and air or surface launched stand-off weapons saturation attacks. The system is designed for fully autonomous operation within the Integrated Battle Command System (IBCS) framework, with advanced artificial intelligence and machine learning (AI/ML) algorithms for threat classification, engagement sequencing, and fire control. Real-time networking between fire units enables distributed sensor-shooter architectures, cooperative engagements, and dynamic sector management across the battlespace.

Turret:
The RBS 85 turret is mounted via a 1,575mm diameter turret ring compatible with various carrier vehicles. The interface ring includes a 360° continuous rotation slip ring for power (3-phase 400 Hz, 28 VDC), fiber-optic data bus, high-speed Ethernet (10 GbE), fiber-optic sensor data links, and liquid coolant supply/return lines. The turret drive system employs dual brushless DC motors with harmonic drive gear reduction, providing a maximum traverse rate of 120°/s and an elevation rate of 80°/s. A precision encoder system provides 0.01-mil pointing accuracy. The turret iself is a fully enclosed, low-profile turret assembly constructed from welded aluminum 7039 alloy with composite armor applique panels. The turret houses the complete fire control system, missile launchers, radar antenna, and EO/IR sensor suite in a single integrated assembly weighing approximately 4,000 kg (fully loaded with eight missiles). The turret envelope measures 2.1 meters wide, 2.4 meters deep, and 0.95 meters tall (from turret ring to roof), maintaining a low visual and radar signature profile. The turret features a modular architecture with four primary subsystem bays accessible through armored maintenance panels: the radar electronics bay (forward-left), the fire control computer bay (forward-right), the EO/IR sensor bay (center-front), and the power conditioning and cooling bay (rear-center). This modular layout enables field replacement of major subsystems within 90 minutes using standard organizational-level tools.

The turret carries eight Rb 85 missiles arranged in two quad-stack launcher assemblies positioned on either side of the central sensor pod. Each quad-stack launcher consists of four sealed launch tubes arranged in a 2×2 configuration, with each tube serving as both the shipping/storage container and the launch rail. The sealed tube design protects the missiles from environmental exposure, electromagnetic interference, and battle damage fragmentation throughout the system’s operational life. The launcher assemblies are mounted on a common elevation cradle that provides +85/-10° of elevation travel independent of the turret’s azimuth rotation. The elevation mechanism uses a dual-screw electric actuator with redundant motor drives and a fail-safe mechanical lock. Missile tubes can be individually selected and fired in any sequence, with a minimum inter-launch interval of 0.5 seconds to prevent exhaust interference between adjacent missiles. Reload is accomplished using a dedicated ammunition resupply vehicle equipped with a hydraulic crane and guided rail system. A trained crew of three can reload all eight tubes in less than 12 minutes under field conditions. Tubes are replaced as complete sealed rounds, the missile is factory-sealed into its launch tube and never handled separately, eliminating the need for alignment procedures or electrical connector mating in the field.

The turret systems require approximately 18 kW of continuous electrical power during full combat operations (radar transmitting, EO/IR active, fire control computing), reducible to 6 kW in a reduced-power silent watch mode where the radar operates in a passive listening/low-probability-of-intercept mode and the EO/IR system performs periodic scanning. The integrated liquid cooling system provides 12 kW of thermal rejection capacity through a closed-loop ethylene glycol/water circuit with redundant circulation pumps and an air-cooled heat exchanger mounted on the carrier vehicle’s rear hull. The turret applique armor provides ballistic protection against 12.7×99mm AP rounds at 100 meters and 152/155 mm shell splinters at 25 meters across all surfaces. Additional survivability features include an automatic fire detection and suppression system and laser warning receivers integrated into the vehicle’s countermeasures suite.

Rb 85 Interceptor
Weight: 85 kg
Length: 2.4 m
Diameter: 165 mm
Propulsion: Dual-pulse solid fuel rocket
Operational Range: 0.5-16 km
Intercept Altitude: 0- 8 km
Speed: Mach 5.5
Warhead: 12.5 kg dual-mode self forging fragment
Guidance: laser beam-riding
Steering: Thrust-vectoring, control fins
Launcher: Turret based launcher with eight canisters
The Rb 85 interceptor is a short range hypervelocity surface-to-air missile which is used with the RBS 85 air defense system. The missile is 2.4 meters long, 165 mm in diameter, and weighs 85 kilograms. The missile contains a 12.5 heavy metal dual mode self-forging fragment (SFF) warhead which is able to produce either large, high velocity self-forging tantalum alloy self-forging fragments for use against armored fixed and rotary wing targets or larger numbers of smaller tantalum alloy fragments for use against unarmored or smaller targets. Warhead detonation is triggered by an active laser proximity fuze with low-altitude clutter rejection and small target sensing capability. The missile is powered by a smokeless solid-fuel boost-sustain type rocket motor and has a maximum velocity of mach 5.5 (1,600 m/s) with a time-of-flight of 7 seconds to 8 km, 10 seconds to 10 km, and 13 seconds to 12 km. The missile steers using an integrated aerofin thrust vector control (IATVC) with pneumatically actuated tail control fins and jet vanes which provides the missile with 70 g overlord capability out to 8 km, 45 g out to 10 km, and 25 g out to 12 km. The missile is guided using a laser beam-riding system. The missile’s aft-mounted laser receiver assembly consists of four quadrant detectors placed in the missile's four tail fins, detecting the modulated laser beam and generating proportional navigation error signals. The onboard guidance electronics process these signals through a Kalman filter to compute steering commands, which are executed by four tail control surfaces The guidance system achieves a terminal miss distance of less than 1 meter against maneuvering targets, sufficient to bring the laser proximity fuze and warhead within lethal radius against all target categories. The missiles are contained within sealed fiberglass launch canisters which are 2.6 m long, 0.24 m in diameter and weigh approximately 100 kg loaded and 15 kg empty. The launch canisters feature internal thermal liner and a frangible forward cover that is blown clear by the missile’s booster charge upon ignition.

FMG 100 Surveillance Radar
Frequency:
8-10 GHz (C band)

Antenna technology:
Active Phased Array, GaN Tx/Rx modules

Antenna rotation rate:
60 RPM

Instrumented range:
75 km

Azimuth:
360°

Elevation:
-10° to +70°

Target Capability:
100 simultaneous
Each RBS 85 fire unit is equipped with an SDI FMG 100 VSHORAD (Very Short Range Air Defense) radar, an X band (8-10 GHz), digital stacked beam 3D air-surveillance radar which provides three-dimensional, 360° detection, tracking, and target handover of fixed and rotary wing aircraft, missiles, and UAV targets while stationary and on-the-move in high-clutter and ECM heavy environments. The radar employs a fully digital active electronically scanned array (AESA) antenna with a total of approximately 1,500 air-cooled GaN-on-diamond Tx/Rx elements each with integral digitizers and a common digital beamformer. The antenna can be scanned electronically ±60° in both azimuth and elevation from the array boresight. Full 360° azimuth coverage is achieved through mechanical rotation of the turret, with the radar performing a complete hemispheric search scan every 2 seconds during normal operation and a focused sector scan with a revisit rate of 0.5 seconds when cued by external sensors or directed by the fire control system. The radar can simultaneously form up to four independent tracking beams while maintaining search operations. The radar has an instrumented range of 75 kilometers and can detect a 1 m2 RCS target at 40 kilometers and a 0.01 m² RCS target at 15 kilometers in search mode. Track capacity is up to 100 simultaneous tracks with 10 simultaneous precision fire-control quality tracks. The radar’s signal processing architecture is built around a ruggedized, liquid-cooled multi-core digital signal processor delivering 50 TFLOPS of sustained throughput. This processing capacity supports real-time adaptive beamforming, space-time adaptive processing (STAP) for ground clutter suppression during on-the-move operations, and the AI/ML-based automatic target classification engine. The classification engine uses micro-Doppler signature analysis and high range resolution (HRR) profiling to distinguish between threat categories including differentiating small UAS from birds, decoys from actual threats, and manned from unmanned aircraft without requiring external database updates.

The FMG 100 radar incorporates a comprehensive electronic counter-countermeasures (ECCM) suite designed to maintain operational effectiveness in dense electronic warfare environments. Key features include wideband instantaneous frequency agility across 2.2 GHz of bandwidth, pulse-to-pulse frequency hopping with over 4,000 agility channels, ultra-low antenna sidelobes (-45 dB peak sidelobe level), sidelobe blanking and cancellation using dedicated auxiliary antennas, and an intelligent power management system that minimizes emissions to the lowest level consistent with the current tactical situation to reduce susceptibility to anti-radiation missile threats. Further active ECCM features of the radar include sidelobe cancellation (SLC), pulse/pulse and burst/burst frequency agility, random PRF switching, and low power frequency modulated continuous wave (FMCW) modes for low probability of intercept/detect (LPD/LPI) operation. An L-band (1 to 2 GHz) Identification Friend or Foe (IFF) antenna is also included in the radar to allow for interrogation of air vehicles, which is also capable of displaying track information on up to 10 prioritized targets on the radar operator's display. The radar is mounted on an extendable mast and can fold back into the turret when not in use.

Electro-Optical Missile Fire Control Sensor System
The RBS 85 electro-optical integrated missile fire control sensor contains FLIR, TV, and laser systems and is capable of automatic sector based passive IR surveillance, automatic and manual passive day/night passive target tracking, and automatic missile tracking and fire control. The sensor is housed in a stabilized, gimballed sensor turret mounted on the centerline of the turret forward face, directly between the two quad-stack launcher assemblies. The sensor turret provides continuous rotation in azimuth and ±90° of elevation, with high-bandwidth direct-drive torque motors providing stabilization accuracy of better than 15 microradians RMS in all axes during on-the-move operations. The primary FLIR sensor uses a third-generation 1280×1024 pixel Mercury Cadmium Telluride (MCT) focal plane array operating in the long-wave infrared (LWIR) 8–12 μm band with integrated Stirling-cycle cooling. The sensor provides a narrow field of view (NFOV) of 1.0° × 0.8° for long-range precision tracking, a medium field of view (MFOV) of 4.0° × 3.2° for target acquisition, and a wide field of view (WFOV) of 12.0° × 9.6° for situational awareness and search operations. The FLIR is capable of detecting fighter size targets at ≥30 km (afterburner) or ≥20 km (cruising), Group 3 UAS at ≥12 km, and Group 1 UAS at ≥5 km. A high-resolution low-light TV camera uses a 4096×4096 pixel CMOS sensor with a continuous-zoom optical system providing fields of view from 0.5° to 30°and includes an automatic gain control, electronic image stabilization, and a high-dynamic-range mode for operation in challenging lighting conditions including dawn/dusk transitions, snow glare, and desert haze. The missile guidance laser is a high-power, modulated solid-state laser operating at 1.064 μm wavelength, providing the coded laser beam for beamriding guidance of the Rb 85 missile. The beam is precisely steered to the predicted intercept point by the fire control system, with the missile riding the beam to the target. The laser provides a coded beam with >256 unique modulation codes to prevent mutual interference between adjacent fire units and resist enemy laser jamming. Beam divergence is actively controlled between 0.5 and 8.0 milliradians depending on engagement phase. An eye-safe erbium-glass laser operating at 1.57 μm, providing precision ranging to 20 km with ±5 meter accuracy.

Once a target has been detected by the system's search radar the turret is automatically slewed towards the target bearing and a search is initiated to bring it into the field-of-view of the FLIR and TV camera sensors. The target is then tracked by either or both FLIR and TV sensors which lock-on to the target and begins automatic tracking. The range to the target is measured either by the Holmium laser rangefinder or by the track-while-scan function of the surveillance radar to ensure that the target is within engagement range. A missile is then launched and guided by a coded pulse laser to the target. An additional near-infrared tracker is used to align the boresight of the guidance laser with the FLIR and TV sensors before the missile is captured by the guidance laser approximately 500 meters after launch. When not in use the entire electro-optical sensor module can rotate backwards to protect the optical sensors from hostile fire.

Fire Control System
The RBS 85 fire control system is built around a ruggedized, liquid-cooled high-performance embedded computing platform. The fire control computer integrates inputs from the radar, EO/IR suite, external battle management system (BMS) data links, and onboard inertial navigation systems to generate real-time fire control solutions against multiple simultaneous targets. The computing platform features a multi-processor architecture delivering 200+ TFLOPS of heterogeneous computing throughput, combining general-purpose CPU cores for fire control algorithms with GPU and FPGA accelerators for AI/ML inference, sensor fusion, and real-time image processing. The system runs a real-time operating system (RTOS) with deterministic latency guarantees of less than 1 millisecond for critical fire control loop functions.

The RBS 85 is designed to operate in three engagement authority modes:

Mode 1 – Fully Automatic: The system autonomously detects, classifies, identifies, and engages all targets meeting the pre-programmed engagement criteria without human intervention. Human override and abort capability is maintained at all times. This mode is intended for high-density threat environments where the reaction time required precludes human-in-the-loop decision-making.

Mode 2 – Semi-Automatic: The system autonomously detects, classifies, and identifies targets, then presents engagement recommendations to the operator for approval. Upon operator consent, the system executes the engagement autonomously. This is the default operational mode.

Mode 3 – Manual: The operator manually designates targets using the EO/IR system or selects radar tracks for engagement. The fire control system computes the engagement solution and executes upon operator command. This mode provides maximum positive human control for operations in complex airspace environments.

A typical engagement cycle stars as the radar detects and initiates track on new contact (0.0 seconds). An automatic classification engine analyzes radar return and assigns preliminary threat category (0.0–1.5 seconds). IFF interrogation is then performed, target correlated with air picture from BMS data links (1.0–2.5 seconds). If target classified as hostile, EO/IR sensor slews to target bearing for visual confirmation and precision tracking (1.5–3.0 seconds). Fire control solution is then computed; warhead mode selected, engagement recommendation is presented to operator or auto-executed per engagement authority mode (3.0–4.0 seconds). Missile is launched, guidance beam locked to predicted intercept point (4.0–4.5 seconds). Missile flight and terminal guidance is performed, continuous fire control updates sent to guidance beam (4.5 seconds to impact). Kill assessment is performed via radar track and EO/IR observation, re-engagement decision if required (impact + 2.0 seconds). Total reaction time from initial detection to missile launch is less than 5 seconds in fully automatic mode and less than 8 seconds in semi-automatic mode with a trained operator. The fire control system incorporates advanced artificial intelligence and machine learning algorithms for threat assessment and engagement optimization. The AI/ML engine fuses data from the radar (including micro-Doppler analysis, ISAR imaging, and RCS measurement), EO/IR sensors (including automatic target recognition from thermal and visible imagery), and external intelligence feeds to produce a comprehensive target classification with associated confidence levels. The engagement optimization algorithm considers remaining missile inventory, threat priority rankings, probability of kill estimates for each available engagement option, and coordination with adjacent fire units to recommend optimal engagement strategies. In multi-target scenarios, the algorithm performs combinatorial engagement planning to maximize the probability of defending all critical assets within the system’s defended area.

Fire Control System
The RBS 85 is designed as a native node within a Battle Management System architecture, functioning as both a sensor contributor and a shooter within the distributed IADS (Integrated Air Defense System) network. The system’s BMS interface enables seamless integration with broader air and missile defense enterprise, including RBS 73 and RBS 81 systems. The BMS interface
provides reception of external track data and cueing from higher-echelon sensors, including ground-based radars, airborne early warning platforms, and space-based sensors, contribution of own-sensor track data to the IBCS common track picture, enabling other IAMD nodes to leverage the RBS 85 system's radar and EO/IR data for their own engagements, Engagement coordination with adjacent fire units to prevent double-engagement of the same target and enable distributed fires, and remote engagement authority, allowing a higher-echelon commander to authorize or prohibit specific engagements through the IBCS network. In addition to the BMS tactical data link, fire units within a RBS 85 battery communicate via a dedicated high-bandwidth, low-latency radio data link operating in the C-band with directional mesh networking. This inter-unit link provides less than 10 milliseconds of end-to-end latency for fire coordination messages and supports data rates of 100+ Mbps for real-time sharing of raw sensor imagery and uncompressed track data. The inter-unit data link enables the following advanced cooperative engagement modes:

Distributed Sensor Netting: Multiple fire units share raw radar and EO/IR data to create a fused composite track picture with improved accuracy, reduced track latency, and enhanced detection of low-observable targets through spatial diversity gain.

Cooperative Engagement: Two or more fire units simultaneously engage a single high-priority target, with each unit guiding its missile on an independent intercept trajectory to maximize the probability of kill against highly maneuverable or hardened targets.

Shoot-Look-Shoot Coordination: Fire units coordinate sequential engagements against the same target, with the first shooter’s kill assessment informing the second shooter’s decision to engage, conserving ammunition while maintaining high overall kill probability.

Sector Management: Fire units dynamically assign and trade responsibility for azimuth sectors and altitude bands based on their current orientation, ammunition state, and sensor health, ensuring continuous 360°coverage of the defended area even as individual units displace or undergo maintenance.

Each RBS 85 fire unit is equipped with a comprehensive communications suite that includes VHF/UHF radios for voice communication and legacy data links, an L-band tactical data link modem for BMS connectivity, the C-band inter-unit mesh radio, a Blue Force Tracker terminal for position reporting and situational awareness, and a Satellite Communications (SATCOM) terminal for beyond-line-of-sight coordination with higher headquarters.

SDI Air Defense System Catalog [DO NOT POST]

SDI Air Defense System Catalog [DO NOT POST]

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