Beyond Gravity (ex-RUAG Space)

Updated 30 Jul 2026

Manufacturer Switzerland Listed

52 Products

33 Years Active

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About Beyond Gravity (ex-RUAG Space)

RUAG Space (part of RUAG Group, now rebranded as Beyond Gravity) is a Swiss aerospace company with facilities in Switzerland, Sweden, Austria, and the US. The company manufactures satellite structures (composite panels, brackets), thermal insulation (MLI blankets), payload electronics, and reflector antennas for ESA, NASA, and commercial satellite programs. RUAG Space has contributed components to Ariane 5, Vega, Sentinel, and hundreds of satellites.

Milestones

1993 RUAG Space division established
2022 Rebranded as Beyond Gravity

Company Info

Headquarters Zurich, Switzerland, Switzerland

Founded 1993 (33 years)

Specializations

satellite manufacturing space structures

Website beyondgravity.com ↗

Email info@beyondgravity.com

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Products

Flight-proven

Low-cost, easy-to-integrate 2-axis thruster gimbal for electric propulsion, supporting 1 to 5 kW thrusters within a 15 degree pointing cone.

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Axes	2-axis pointing mechanism
Thruster power range	1 to 5 kW
Pointing range	15 degree cone
Integration	Simple integration without zero gravity devices
Variants	APPMAX2-H (50 kg thruster, with hold-down and release mechanism), APPMAX2-S (downscaled, in preparation)
Thruster types supported	Hall effect and ion thrusters
Repeatability	better than 0.1°
Thruster Mass	8-15 kg
Mass	13.8 kg
Stiffness stowed	110 Hz
Stiffness stowed, with opt. Damping	80 Hz
Stepper Motor Phase Resistance at 20°C	82 Ω

Flight-proven

Modular deployable 3-axis thruster gimbal driven by three stepper-motor actuators, with micrometeorite-shielded piping and zero-G device.

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Actuation	Three stepper motor-based actuators
Configuration	Modular deployable thruster mechanism with robotic arm deployment
Protection	Micrometeorite shielding on piping; thermal and micrometeorite protection for actuators
Thermal control	Flow controller with radiators and/or MLI per thermal analysis
Mounting	Direct hard mounting baseline; elastomer dampers optional
Position reference	Redundant switches; zero-G device provided
Motion Range	up to 230°
Repeatability	+/- 0.1°
Thruster Mass	1x 12 kg (single Thruster)
Thruster Mass (2)	2x 12 kg (dual Thruster)
Mass	approx. 28 kg
Dimensions	up to 2 m boom length
Stiffness stowed	> 100 Hz
Stiffness stowed, with opt. Damping	> 80 Hz
Stepper Motor Phase Resistance at 20°C	90 Ω
HDRM I/F	8 A at 26 V ca. 200 ms

Flight-proven

Beyond Gravity offers a range of separation systems, dispenser systems, and modular payload adapters designed to securely connect satellites to launch vehicles and precisely deploy them in orbit with a 100% success rate over 1200 in-orbit separations.

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Flight record	More than 1200 in-orbit separations
Success rate	100%
Espa separation system (psr 1575 mm) compatibility	Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA)
Pas 381s (15”) separation system compatibility	ESPA 15” adapter interface
Pas 432s (17”) separation system satellite mass	Up to 200 kg @ 0.45 mm
Pas 432s (17”) separation system launch vehicle	VEGA
Pas 610s (24”) separation system compatibility	Moog CSA ESPA and environments from the ESPA Rideshare User’s Guide
Separation nut psm 1/2b satellite mass	Typical 500-1000 kg
Separation nut psm 3/8b satellite mass	Typical 100-200 kg
Payload adapter materials	Aluminum or carbon fiber composites
Payload adapter launch vehicle compatibility	Alpha, Antares, Ariane, Atlas, Delta, Falcon 9/H, New Glenn, Vega C, Vulcan

Software-defined drive electronics with a radiation-tolerant microcontroller, expanded sensing and in-orbit software patching.

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Architecture	Fully software-defined, radiation-tolerant microcontroller
Command interface	Dual UART; CCSDS command and telemetry packets
Optional extension boards	Signal multiplexing, MIL-STD-1553B communication interface
Sensing	Direct acquisition of analog and digital sensor inputs (motor current, position indicators, end-switches, temperature)
Software maintenance	In-orbit software patching
Form factor	Compact, stackable (same as CODE)
Start-up time	<500 ms
Motor drive voltage	max. 32 V
Motor current	max. 1 A
Stepping rate	max. 1000 steps/s
Standby power consumption	< 3 W
Motor driver efficiency	>75%
Failure rate	<350 FIT (Class 1 parts)
Size	200 x 125 x 31 mm³
Weight	< 0.8 kg
Operating temperature	-30°C to +65°C (qual)
Non-operating temperature	-40°C to +75°C (qual)
Minimum switch-on temperature	-30°C
Fundamental Frequency	> 550 Hz
Random vibration	18.4gRMS
Radiation	up to 50 kRAD (Si)
Supply voltage	22 V to 38 V
Interface	DUAL-UART RS-422

Modular C-, Ku- and K-band frequency converters and receivers for telecom payloads, using MMIC and hermetic LTCC hybrid miniaturization.

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Frequency plans	C to C, C to Ku, Ku to C, Ku to Ku, K to Ku band
Cross links	Supported between C- and Ku-band
Technology	MMIC and hermetic LTCC hybrid miniaturization
Interfaces	Configurable DC-power and TM/TC interfaces
Application	FSS/BSS telecom payloads
Frequency range Input C-band	5.8-7.0 GHz
Frequency range Input Ku-band	12.75-14.80 GHz
Frequency range Input K-band	17.3-18.4 GHz
Frequency range Output C-band	3.4-4.8 GHz
Frequency range Output Ku-band	10.70-12.75 GHz
Frequency range Output	13.4-13.65 GHz
Gain	20-35 dB (Converter version)
IP3	33 dBm
Noise figure	1.4 dB (C-band Receivers)
Phase noise	-120 dBc/Hz @ 10 kHz (LO = 3.3 GHz)
Operating temperature	-20°C to + 70°C
Supply voltage	28-100 V
Power	10 W
Mass	0.7 kg (Converter)
Dimensions	140 x 50 x 92 mm (Converter)
RF input Interface	SMA (Converter and C-band Receiver)
RF output Interface	SMA

Composite payload fairings from 0.7 m to 5.4 m diameter, used on Ariane, Vega, Atlas, Vulcan and H3, with a 100% success rate over 400+ launches.

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Diameter range	0.7 m to 5.4 m
Construction	Aluminium honeycomb core with carbon fibre reinforced composite cover layers
Manufacturing	Automated industrial process, no autoclave required
Flight record	Over 400 launches, 100% success rate
Launch vehicles	Ariane, Vega, Atlas, Vulcan, H3
Launch site support	Separation dynamics measured, transmitted to ground control and analysed

Flexible high-temperature vacuum insulation for launchers up to 550 degrees C, free of hazardous components and tunable to customer requirements.

Maximum temperature	Up to 550 degrees C
Type	High temperature vacuum insulation, conductive glass fabric
Advantages over ceramic fabrics	Greater flexibility, no hazardous components, adjustable performance
Weight	429 g/m2 ±5%
Thickness	0.4 mm ± 5%
Width	1.2 m
Length	10 m
Solar absorptance (αs)	0.08
Thermal emittance (300K)-(ε)	0.93
ESD grid dimension	108 x 108 mm

Flight-proven

Fully redundant on-board computer subsystem built entirely from commercial components, with integrated GNSS receiver and platform/payload interfaces.

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Architecture	Complete subsystem based entirely on commercial components
Redundancy	Fully redundant, flight-proven FDIR
Integrated functions	On-board processing, GNSS receiver, ground communication, platform and payload interfaces
Optional boards	PDIO (analogue interfaces, magnetorquers, thermistors, stepper motors incl. SADE), PROPE (chemical propulsion interface)
Frequency	800 MHz
Processing memory	1 GiB DDR3
Non-volatile storage	2.7 GiB
Temperature	-20 to +60 °C
Random vibration	15 g RMS
Shock	2000 g @ 2000 Hz
Volume	300 x 119 x 239 mm³
Power	~26 W
Mass	5.4 kg
GNSS accuracy	1m 3D RMS
PPS time error	< 100ns RMS
Lifetime	10 years

Customizable remote terminal unit bridging the on-board computer and platform electronic interfaces, based on the same COTS I/O boards as the cOBC.

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Function	Bridge between On-Board Computer and platform electronic interfaces
Board commonality	Same commercial I/O boards as the cOBC
Customization	Additional modifications and new board types available on request
Supply voltage	28 V (22 V – 38 V)
Pulse commands number of pulses	81
Pulse commands pulse voltage	28 V
Pulse commands pulse current	< 0.6 A
Secondary voltages output voltage	5 V
Stepper motors number of motors	4
Stepper motors drive voltage	28 V
Stepper motors drive current	< 0.5 A
Stepper motors end stop inputs	8
Magnetorquers number of bar drives	3
Magnetorquers drive voltage	28 V
Magnetorquers supply channels	4
Magnetorquers end stop inputs	8
Analogue acquisitions input channels	128 / 64
Operating temperature	-20 to +60°C
Random vibration	15 g RMS
Shock	2000 g @ 2000 Hz

Multi-layer vacuum superinsulation line for cryogenic applications, laser-cut to shape, with polyester, aluminium-foil, LOX-compatible and tape variants.

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Coolcat 2 nw	10 layers double-sided aluminized perforated polyester foil interleaved with 10 layers of non-woven polyester spacer; used in serial MRI, NMR and accelerator cryostats
Coolcat 2 nf	Glass fibre fleece spacer with 9 micrometre pure aluminium foil; high temperature tolerant, non-flammable, ISO 21010 tested
Coolcat 2 lox	5 layers pure aluminium foil with 5 layers glass fibre cloth spacer; liquid oxygen compatible, ISO 21010 tested, free of organic constituents
Coolcat 2 ni	Polyester foil aluminized in squares (10x10 mm single-sided or 20x20 mm double-sided) with non-woven polyester spacer; minimizes eddy currents in varying magnetic fields
Coolcat h	Welding protection of aluminium foil and fibre-glass cloth
Coolcat 4k	Low absorptance helium vessel laminate: 6 micrometre pure aluminium foil plus 12 micrometre double-side aluminized polyester foil
Coolcat 1050	80 micrometre high purity (99.5%) aluminium foil tape with pressure sensitive acrylic adhesive
Coolcat b-r50	25 micrometre double-sided aluminized polyester foil low emissivity adhesive tape
Laser cutting envelope	Maximum width 2.7 m, maximum length 3.0 m
Certifications	ISO 9001, ISO 14001, EN 9100 by DNV

Compact, lightweight two-axis stepper motor controller for small satellite mechanisms, built as stackable modules.

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Type	Two-axis stepper motor controller, modular and stackable
Motors per module	Two bipolar stepper motors, independently controlled
Redundancy	Two modules stacked vertically, cold redundancy
Power conversion	Isolated DC/DC converter with EMC filters, hardware-adjustable motor drive voltage
Mechanism signals	7 additional signals per motor connector for sensors (switches, thermistors) or heaters up to 115 V
Motor control interface	3 discrete signals ENABLE / DIRECTION / STEP per motor
Start-up time	<500 ms
Motor drive voltage	18 to 26 V (adjustable)
Motor current	max. 0.5 A
Stepping rate	max. 1000 steps/s
Standby power consumption	< 3 W (typ)
Motor driver efficiency	>75%
Failure rate	227 FIT (Class 1 parts)
Dimensions	190 x 125 x 58 mm³
Mass	< 1.1 kg
Minimum switch-on temperature	-30°C
Radiation	up to 50 kRad (Si)
Supply voltage	22 V to 38 V

Flight-proven

1575 mm (62 in) low-shock clamp band separation system fully compatible with the EELV Secondary Payload Adapter (ESPA).

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Interface diameter	1575 mm (62 in)
Compatibility	EELV Secondary Payload Adapter (ESPA)
Release mechanism	CBOD Low Shock Release Mechanism
Scope of supply	Low shock clamp band separation system, payload separation rings, umbilical connectors, separation spring set
Family diameter range	381 mm to 3100 mm (15 to 122 in)
Flight record	More than 1600 in-orbit separations, 100% success rate (June 2026)

Flight-proven

Coated or laminated ceramic fabric and ceramic felt insulation protecting components near rocket motors and nozzles at up to 1500 degrees C.

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Maximum temperature	Up to 1500 degrees C
Materials	Coated or laminated ceramic fabric and ceramic felt insulators
Application	Components in direct vicinity of rocket motors or nozzles
Density (Ceramic Felt for 1500°C)	100 – 130 kg/m3
Mass (Ceramic Felt for 1500°C, 13mm thickness)	1270 – 1650 g/m2
Mass (Ceramic Fabric for 1500°C)	510 g/m2
Mass (Aramid Fabric)	280 g/m2
Mass (Protective Coating)	30 – 120 g/m2
Thermal Conductivity (Felt, 13mm, 25°C)	0.04 W/(mK)
Thermal Conductivity (Felt, 13mm, 750°C)	0.18 W/(mK)
Thermal Conductivity (Felt, 13mm, 1500°C)	0.33 W/(mK)
Thermal Conductivity (Felt-Fabric compound, 14mm, 25°C)	0.04 W/(mK)
Thermal Conductivity (Felt-Fabric compound, 14mm, 750°C)	0.16 W/(mK)
Thermal Conductivity (Felt-Fabric compound, 14mm, 1500°C)	0.33 W/(mK)

Flight-proven

3U SpaceVPX modular avionics platform (Flexible On-board avioniX) of off-the-shelf modules for LEO, MEO, GEO and cislunar missions.

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Form factor	3U SpaceVPX modular platform
Target orbits	LEO, MEO, GEO and cislunar
Communication	Ethernet-based, supporting redundancy and high data rates
Applications	Spacecraft control, edge/payload processing, payload and robotics control, GNSS receiver, cloud computing
Operating temperature	-20…+60 °C
Lifetime	10+ years
Radiation tolerance (TID)	> 36 kRad
Random vibration	15 g RMS
Shock	2000 g @ 2000 Hz

Cost-efficient, optionally redundant software-defined GNSS receiver for commercial GTO/GEO missions, accurate to below 10 m 3D rms.

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Constellations	GPS, Galileo
Target orbits	GTO / GEO
On-board navigation accuracy	Below 10 m 3D rms
Mission duration	Up to 15 years
Architecture	Software-defined radio (SDR); redundant or non-redundant configuration
Mass	4 kg
Dimensions	217x148x131mm3
Power consumption	< 10 W
Supply voltage	28 V
Lifetime	10 years
Position Accuracy	< 10 m 3D typ.
Velocity Accuracy	< 1 cm/sec 3D rms
Time Accuracy	< 0.5 µsec 1 sigma
Interfaces	2 antenna inputs
Interfaces (2)	2 UARTs (RS-422)
Interfaces (3)	2 outputs (RS-422)
Total Ionisation Dose	36krad
Time-to-first fix	< 15 min

Flight-proven

Next-generation multi-frequency, multi-constellation GNSS receiver built on commercial components, with optional subscription-free PPP.

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Supported GNSS signals	GPS L1 C/A, GPS L2C, GPS L5 I/Q, Galileo E1 B/C, Galileo E5a I/Q, Galileo E6 B/C (optional)
On-board position accuracy	< 1.0 m 3D rms
On-board velocity accuracy	< 2 mm/s 3D rms
Time accuracy	< 50 ns (1 sigma)
Position accuracy with ppp (Galileo-only)	< 0.2 m 3D rms
Velocity accuracy with ppp (Galileo-only)	< 1 mm/s 3D rms
Time accuracy with ppp (Galileo-only)	< 30 ns (1 sigma)
Design lifetime	Up to 10 years in space

High-performance processing unit for payloads, instruments and robotics, with scalable software and gateware processing.

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Function	Control and data processing for payloads, instruments and robotics
Processing	Software and gateware processing, scalable to processing and storage needs
Platform	Part of the FoX Electronics Platform (3U SpaceVPX)
Mass	3.6 kg
Dimensions	148x128x217 mm3
Lifetime	10+ years
Random Vibration	15 g RMS
Shock	2000 g @ 2000 Hz
Interface	2 Ethernet (1000BASE-T, 10/100BASE-TX), 2 SpaceWire (LVDS), 2 UART (RS422/485), Processor Debug (UART + JTAG), FPGA Debu
Memory	4 GiB DDR processing memory with ECC
Non-volatile storage	20 GiB with ECC
Processing performance	> 30.000 DMIPS, >45000 CoreMarks, 58 GFlops

Multi-constellation GNSS receiver for GTO/GEO missions with better than 20 m on-board real-time navigation accuracy in GEO.

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Supported GNSS signals	GPS C/A on L1, Galileo E1 B/C
Signal processing hardware	Dedicated RF and Mixed-Signal ASICs plus AGGA-4 ASIC
Position accuracy in GEO	20.0 m 3D rms
Velocity accuracy in GEO	1 cm/s 3D rms
Time offset 1pps (1 sigma)	< 0.5 microseconds
Tracking capacity	Single-frequency up to 12 satellites
Supply voltage	100 V regulated
Power	15 W avg.
Operating temperature	-30°C to + 60°C
Minimum switch-on temperature	-40°C
Lifetime	15 years
Dimensions	LNA: 168x54x80 mm; Electronic box: 286x201x226 mm; Antenna: 212 mm, h: 179 mm
Mass	LNA: 0.6 kg; Electronic box: 9.0 kg; Antenna: 548 g
Interface	MIL-STD-1553B or UART (RS-422) or SpaceWire; PPS output nom/red/test (RS-422); ON/OFF high level command interface; Ther

Ground support equipment clampband connecting spacecraft interface rings to test adapters during AIT, in PAS 937 S, 1194 VS and 1666 MVS sizes.

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Clampband pas 937 s	Manufactured per Ariane 5 User's Manual (Issue 5 Rev 2), Soyuz User's Manual (Issue 2 Rev 1) and Vega User's Manual (Issue 4 Rev 0)
Clampband pas 1194 vs	Manufactured per Ariane 5 User's Manual (Issue 5 Rev 2) and Soyuz User's Manual (Issue 2 Rev 1)
Clampband pas 1666 mvs	Manufactured per Ariane 5 User's Manual (Issue 5 Rev 2) and Soyuz User's Manual (Issue 2 Rev 1)
Units delivered	More than 50 GSE clampbands
Services	In-house proof load testing without dummy equipment
Operating temperature	-100…+100 °C
Dimensions	1010 × 1125 × 90 mm
Mass	30 kg

Compact Ka-band payload receiver and converter with internal LO generation and EPC for most satellite bus standards.

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Band	Ka-band payloads
Local oscillator	Internal LO generation; adaptable to LO frequencies up to 12 GHz
Power conditioning	Integrated EPC for most satellite bus standards
Technology	Latest MMIC technologies
Frequency range, Input	27.5 - 31.0 GHz
Frequency range, Output	17.7 - 21.2 GHz
LO Frequency range	7 - 12 GHz
Gain (Converter)	27 - 33 dB
Gain (Receiver)	58 - 62 dB
Transmit Band Gain (Converter)	<-20 dB
Transmit Band Gain (Receiver)	< 0 dB
OIP3	32 dBm
Noise figure (Receiver)	< 2.3 dB
Noise figure (Converter)	< 14 dB
Operating temperature	-20°C to + 70°C
Supply Voltage	28-100 V
Power consumption	10 W
Mass	0.77 kg
Dimensions	142 x 104 x 54 mm
RF input	WR34 or WR28 Waveguide
RF output	SMA-K
DC & TM/TC	MDM-25

Flight-proven

Space-qualified Ka-band LNA covering 27.5 to 31 GHz, built on mHEMT MMIC technology, available as single slice or multipack.

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Frequency coverage	27.5 to 31 GHz (full Ka-band)
Technology	mHEMT MMIC
Configurations	Single LNA (Slice) with secondary DC power, or Multipacks up to Quad-packs with secondary DC or internal DC/DC supply
Interfaces	Configurable DC-power and TM/TC interfaces
Flight heritage	Beyond Gravity LNAs have accumulated over 10,000 years of operational time in orbit
Frequency	27.5 to 31.0 GHz
Gain	40 - 60 dB
OIP3	>20 dBm
Noise figure	<2.3 dB
Operating temperature	-20°C to + 70°C
DC power (internal DC/DC)	<2.4 W
Mass	Single Slice: 0.17 kg
Dimensions	Single Slice: 103 x 36 x 52 mm

Multi-constellation single-frequency GNSS receiver for LEO with on-board real-time navigation accuracy below one metre.

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Supported GNSS signals	GPS L1 C/A, Galileo E1 B/C
On-board position accuracy	1.0 m 3D rms
On-board velocity accuracy	2 mm/s 3D rms
Time offset 1pps (1 sigma)	< 50 ns (typ. 25 ns)
Tracking capacity	Single-frequency up to 12 satellites
Time-to-first-fix	Warm start < 90 s; Cold start < 15 min GPS; <40 min GALILEO
Dimensions	280x240x81 mm
Mass	3.0 kg
Operating temperature	-30°C to +60°C
Minimum switch-on temperature	-40°C
Power	15 W avg.
Antenna dimensions	144 mm, h: 36,5 mm
Antenna mass	215 g
Interface	MIL-STD-1553B or UART (RS-422) or SpaceWire
Supply voltage	28 V unregulated

Hybrid stepper actuator with high unpowered detent torque, planetary gear and high-load output bearings for electric propulsion pointing mechanisms.

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Motor type	Hybrid-type stepper motor with high detent torque
Gear	Planetary gear
Bearings	High-load output bearings
Unpowered behaviour	High unpowered detent torque; holds pointing position under high back-driving torques
Design basis	Beyond Gravity modular actuator system
Application	Electric propulsion pointing mechanisms (EPPM)

Flight-proven

Dual-redundant master local oscillator for telecom payloads with compact design for 7 to 13 GHz output.

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Output frequency	7 to 13 GHz
Redundancy	Dual-redundant
Flight heritage	LO from Beyond Gravity Converters and Receivers
Interfaces	Configurable output frequencies, DC and TM/TC interfaces; compatible with most satellite bus standards
Frequency	7 - 13 GHz
Phase Noise (10 Hz offset)	-50 dBc/Hz
Phase Noise (100 Hz offset)	-80 dBc/Hz
Phase Noise (10 kHz offset)	-105 dBc/Hz
Phase Noise (1 MHz offset)	-115 dBc/Hz
Phase Noise (>10 MHz offset)	-115 dBc/Hz
X-tal harmonics	-100 dBc
LO Harmonics	-30 dBc
Operating temperature	-20°C to + 70°C
Power	<10 W
Supply voltage	28-100 V
Mass	1.3 kg
Dimensions	122 x 86 x 120 mm
Interface (RF Output)	coaxial SMA

Flight-proven

Modular aluminium or carbon-fibre payload adapters compatible with Alpha, Antares, Ariane, Atlas, Delta, Falcon 9/H, New Glenn, Vega C and Vulcan.

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Materials	Aluminium or carbon fibre composites
Launch vehicle compatibility	Alpha, Antares, Ariane, Atlas, Delta, Falcon 9/Heavy, New Glenn, Vega C, Vulcan
Separation record	More than 1200 in-orbit separations, 100% success rate
Offering	Off-the-shelf products and tailor-made solutions
Diameter	360 mm to 3100 mm
Separation success rate	100 %

Tiltable and rotatable MGSE trolley supporting spacecraft during horizontal or vertical integration, with a full set of EC safety interlocks.

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Motion	Table tilts and rotates to any attitude between spin axis vertical and horizontal
Spacecraft interface	Transport and Handling Adapter (THA) or other test adapters
Materials	Aluminium alloy or carbon steel
Safety	EC-compliant interlocks: no rotating while tilting, no tilting while rotating, key-switch mains power, overload limitation
Units delivered	Over 80 Multi-Purpose Trolleys in Europe and the USA
Cleanliness	Class ISO 8 (ISO 14644-1)
Tilting Range	0° - 90° / 90° - 96°
Tilting Speed	Nominal 6 min from 0° - 90°
Slewing Range	0° - 360°
Slewing Speed	Nominal 8 min for one full rotation
Dimensions	6255 × 2945 × 1544 mm (I/F plane horizontal, on Castors)
Dimensions (2)	6255 × 2945 × 4260 mm (I/F plane vertical, on Castors)
Height of S/C axis	3170 mm (I/F plane vertical)
Mass empty	8730 kg
SWL	5400 kg
Rated Tilt Moment	181.7 kNm
Max. allowable out-of-balance moment	6.7 kNm
S/C max. length	8750 mm
S/C max. cylindrical shape	Ø 4880 mm (0° - 90°)
S/C max. cylindrical shape (2)	Ø 4470 mm (90° - 96°)
S/C max. rectangular shape	4470 x 1800 mm

High-performance two-axis stepper motor controller for satellite mechanisms, optimized for low micro-vibration operation.

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Type	Two-axis stepper motor controller
Redundancy	Two electrically identical units for cold redundancy
Command interface	MIL-STD-1553 TC/TM (replaceable to suit platform concept)
Power conversion	Isolated DC/DC converter per unit; available for different power bus voltages
Driven mechanisms	Antenna pointing mechanisms, solar arrays, thruster pointing mechanisms
Optimization	Low micro-vibration operation
Start-up time	<500 ms
MIL-1553 TM rate	up to 16 Hz
Motor Drive voltage	up to 60 V
Drive current	up to 1 A, 8-bit
Motor speed	0 - 750 full-steps per second
Thermistor acquisition	1.3°C in a range of -50° to +140°C
Potentiometer acquisition	0.07% full-scale, 12-bit
Speed jitter	<0.02%
Standby power consumption	< 8 W
Motor driver efficiency	>75%
Failure rate	< 820 FIT per redundant unit
Magnetic moment	< 0.015 Am2
Dimensions	300x250x123 mm
Mass	< 5 kg
Operating temperature	-30°C to +60°C

Payload-agnostic 150-250 kg LEO platform with electric propulsion, ~1 kW power, low-drag profile and stackable multi-launch configuration.

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Total mass	150-250 kg
Power	Designed with 1 kW and more
Design life	Approximately 7 years in LEO
Internal payload bay	1000 mm x 170 mm x 470 mm
Additional payload volume	In +Z and -Y directions
Propulsion	Electric propulsion
Launch configuration	Stackable for multi-launch; compatible with heritage and new small launchers

GNSS receiver function integrated into Beyond Gravity's next-generation on-board computer (cOBC), needing only an external antenna.

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Supported GNSS signals	GPS L1 C/A, Galileo E1 B/C
On-board position accuracy	1.0 m 3D rms
On-board velocity accuracy	25 mm/s 3D rms
Time accuracy (1 sigma)	< 100 ns
Integration	GNSS function embedded in Beyond Gravity cOBC; only external hardware is the antenna
Time accuracy	< 100 ns
Time to first fix (Warm start)	< 150 s (90%)
Time to first fix (Cold start)	< 270 s (90%)
Power	< 1 W
Antenna diameter	Ø144 mm
Antenna mass	216 g
Interface	2 antenna inputs (1 nominal + 1 redundant)

Flight-proven

Radiation-hardened satellite on-board computer built around the Beyond Gravity CREOLE chip with fault-tolerant SPARC V8 processor.

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Core ASIC	Radiation-hardened CREOLE chip developed by Beyond Gravity
Processor	Fault-tolerant SPARC V8
Integrated functions	Communication functions, reconfiguration function, mass memory controller, extension possibilities
Dimensions	283 x 242 x 278 mm
Mass	9 kg
Power	< 38 W
Lifetime	up to 20 years
Processing memory	512 MiB w EDAC
File/Data storage	2 x 374 Gbit w EDAC
Interface	2 x 7 SpaceWire; 2 x 2 Control Area Network (CAN) buses; 2 x 2 Redundant MIL-STD-1553B buses; 2 x 2 Pulse Per Second (PP
Supply voltage	28 V, 50 V or 100 V
Frequency	75 MHz
Processing performance	93 DMIPS
Instruction cache	32 Kbytes
Data cache	16 Kbytes
Boot PROM	32 KiB
SW Image Storage	8 MiB

Flight-proven

Smallest member of the low-shock separation system family, developed to fit the ESPA 15 inch adapter interface.

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Interface	ESPA 15 in adapter interface
Release mechanism	CBOD-LT Separation System Release Mechanism
Scope of supply	Low shock clamp band separation system, interface rings, umbilical connection, separation spring set
Family diameter range	360 mm to 2624 mm (14 to 103 in)
Flight record	More than 660 in-orbit separations, 100% success rate
Bolt pretension (nominal)	11 kN
Mass	3.7 kg
Separated mass	0.98 kg
Height	79 mm
Passive ring	24 x 1/4 inch bolts placed on a diameter of 381 mm (15 inch ESPA I/F)
Active ring	24 x 1/4 inch bolts placed on a diameter of 381 mm (15 inch ESPA I/F)
Initiator type	Pacific Scientific 103377-449
Number of springs	4 to 24 pcs
Spring energy	1.1 Joule
Release type	Low shock < 100 g's @ 1 kHz
Shock output	Low shock < 100 g‘s @ 1 kHz

Flight-proven

Low-shock clamp band separation system designed for satellites up to 200 kg at 0.45 mm on the VEGA launch vehicle.

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Interface diameter	432 mm (17 in)
First application	Satellites up to 200 kg at 0.45 mm on the VEGA launch vehicle
Release mechanism	CBOD-LT Separation System Release Mechanism
Scope of supply	Low shock clamp band separation system, interface rings, umbilical connection, separation spring set
Flight record	More than 660 in-orbit separations, 100% success rate
Bolt pretension (nominal)	15 kN
Mass	7.2 kg
Separated mass	1.9 kg
Dimensions Height	123 mm
Initiator type	Pacific Scientific 103377-449 Hi-Shear PC23-250 ASI PD22240024-009 USI 1F01084-1
Separation springs No. of springs	6 pcs
Spring energy	4.7 Joule
Shock output	< 100 g‘s @ 1 kHz

Flight-proven

Low-shock separation system whose load capability is fully compatible with the Moog CSA ESPA and the ESPA Rideshare User's Guide environments.

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Interface diameter	610 mm (24 in)
Compatibility	Moog CSA ESPA; ESPA Rideshare User's Guide environments
Release mechanism	CBOD-LT Separation System Release Mechanism
Scope of supply	Low shock clamp band separation system, interface rings, umbilical connection, separation spring set
Flight record	More than 660 in-orbit separations, 100% success rate
Bolt pretension (nominal)	15 kN
Mass	5.8 kg
Separated mass	1.0 kg
Dimensions Height	73 mm
Interface Passive ring	36 x 1/4 inch bolt holes on a diameter of 609.6 mm (24 inch, ESPA Grande)
Interface Active ring	36 x 1/4 inch bolt holes on a diameter of 609.6 mm (24 inch, ESPA Grande)
Initiator type	Pacific Scientific 103377-449 Hi-Shear PC23-250 ASI PD22240024-009 USI 1F01084-1
No. of springs	4 to 10 pcs
Spring energy	4.7 Joule
Release type	CBOD-LT
Shock output	Low shock < 100 g‘s @ 1 kHz

High-performance spaceborne GNSS receiver with real-time navigation below 20 cm and Precise Orbit Determination to a few centimetres.

1 7

Supported GNSS signals	GPS L1 C/A, GPS L2C, GPS L5 I/Q, Galileo E1 B/C, Galileo E5a I/Q, Galileo E6 B/C (optional)
On-board position accuracy	< 1.0 m 3D rms
On-board velocity accuracy	< 2 mm/s 3D rms
Time accuracy	< 50 ns (1 sigma)
Position accuracy with ppp (Galileo-only)	< 0.2 m 3D rms
Velocity accuracy with ppp (Galileo-only)	< 1 mm/s 3D rms
Tracking capacity	Dual-frequency up to 18 satellites, single-frequency up to 24 satellites

Fully redundant remote terminal unit bridging the on-board computer and platform and payload electronic interfaces.

1 8

Redundancy	Fully redundant
Function	Bridge between OBC and platform/payload electronic interfaces
Supported functions	Standard I/O, AOCS, propulsion
Form factor	392 x 242 x 277 mm
Power consumption	15 W
Mass	16.6 kg
In-orbit life-time	15 years
Supply voltage	22 - 37 V

Compact, back-drivable general purpose rotary actuator with more than 110 units in space since 2005 and a simple stepper motor interface.

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Units in space	More than 110; first flight 2005
Production capacity	Up to 50 units per year; in continuous production for 20 years
Interface	Simple stepper motor interface
Mechanical	High torque capacity, safely back-drivable
Typical application	Antenna pointing (other applications possible)
Configuration	Actuator housing, rotating interface, mounting interface, cabling, optional end stop
Output speed range	0 to 1 rev / 12 min
Max. output speed (ground testing)	0.5 °/s
Harmonic drive reduction ratio	160:1
Lifetime	15 years in orbit
Mechanism accuracy	± 0,01°
Coil Resistance @ 20°C	76 Ω ± 10%
Coil Inductance @ 20°C	156.0 mH ± 20%
Number of steps per revolution of motor	360
Unpowered holding torque	≥ 7 Nm
Powered Holding Torque @ 23.4V	≥ 30 Nm
Nominal torque	≥ 25 Nm
External diameter	120 mm
Total length	89 mm
Mass	≤ 2.0 kg
Supply voltage	23.4 V – 28,6 V
Power	≤ 17 W
Operating temperature	- 50°C … + 85°C

Flight-proven

Multi-satellite dispenser systems combining structure, separation, harness and thermal subsystems, flown on Galileo, Radarsat Constellation and Eutelsat OneWeb.

1 8

Subsystems included	Structure, separation system, electrical harness, thermal subsystem
Launch vehicle interface	Dispenser structure bolted to the launch vehicle upper stage
Release	Separation nuts and spring units at each separation node
Harness	Redundant umbilical cables per spacecraft, pyrotechnical initiator harness, instrumentation harness
Options	Beyond Gravity power and sequencing electronics
Programme heritage	Galileo, TerraBella, Radarsat Constellation, Amazon Leo, Eutelsat OneWeb
Mass	less than 150 kg
Compatible satellite mass	700 kg

Flight-proven

Custom satellite MLI blankets for 1 K to 1800 K, with MMOD and ATOX protection options, produced for over 800 satellites.

1 6

Operating temperature	1 K to 1800 K
Protection options	MMOD (micrometeoroid orbital debris) and ATOX (atomic oxygen)
Design process	Electronic 3D models; 3D mock-ups and template fit-checks for complex shapes
Related products	Interfillers, sensors and heaters, thermal analysis and correlation services
Flight heritage	MLI for over 800 satellites across 50 space projects; Euclid, Juice, BepiColombo, Eutelsat OneWeb, Galileo
Production site	Berndorf, Lower Austria

Flight-proven

High-performance honeycomb panels with aluminium or carbon-reinforced face sheets, produced on an industrialized line including a US site in Titusville.

1 8

Panel construction	Honeycomb panels with aluminium or carbon-reinforced face sheets
Configurable parameters	Panel thickness, face sheet material, core density
Production sites	Includes highly automated US site in Titusville, Florida
Insert technology	Automated potting of patented GreDom inserts
Flight heritage	Over 650 OneWeb satellites
Mass	90 kg
Dimensions	up to 5m
Launcher Interface	937 / 1194/ 1666

Pressurized and non-pressurized spacecraft containers with thermal control, dynamic damping and air filtering, certified for air transportation.

1 7

Container types	Hat-off, tilt-lid, door-type roll-in, large An124-compatible, constellation-type
Thermal control	Full active and passive thermal control
Environmental control	Air filtering and drying or N2 purging
Constellation container temperature	19-25 degrees C during operation, -40 to 45 degrees C during transport
Constellation container humidity	Below 65% relH during operation, up to 100% relH during transport
Depressurization	IATA-compliant: breathing units for normal transport, burst discs for emergency
Units delivered	Over 60 spacecraft containers in Europe and the US

Large-format spacecraft transport container from Beyond Gravity's spacecraft container line, for the biggest geosatellites and deep space spacecraft.

1 17

Product line	Beyond Gravity spacecraft containers (SCO)
Thermal control	Full active and passive thermal control
Environmental control	Air filtering and drying or N2 purging
Transport modes	Road, air, long-term storage; certified for air transportation on a wide range of aircraft
Operating temperature	+19°C to +25°C (Operational, inside)
Operating temperature (2)	-40°C to +45°C (Transport, outside)
Humidity	< 65% relH. (Operational, inside)
Humidity (2)	≤ 100% relH. (Transport, outside)
Cleanliness	Class ISO 8 (ISO 14644-1)
Dimensions	6785 × 2765 × 2595 mm (Transport)
Dimensions (2)	9490 × 3765 × 3085 mm (with Towbar / Castors / Jacks)
Required height under hook	7000 mm
Mass empty	5400 kg
Mass with GenSet and ITR (Tare)	9500 kg
Total mass loaded	11000 kg
Payload	1470 kg
S/C Stack Dimensions	5119 × 1074 × 989 mm

Low-shock separation nut for constellation-class satellites of typically 500-1000 kg, qualified per AIAA S-113-2005.

1 14

Target spacecraft class	Constellation class satellites, typically 500-1000 kg
Qualification	AIAA S-113-2005 (former DOD-E-83578A)
Initiators	Dual NSI equivalent (PC23, 103377-191/-449/-500, PD222400024-009, 2-8001140-1, 852420-XX)
Worst-case tests passed	Single 80% initiator, cold case, no o-ring, 150% external load - 100% success
Design feature	Internal mechanical leverage reduces initiator pressure spike and shock; direct drop-in replacement for classical higher shock separation nuts
Bolt pretension (nominal)	50 kN
Mass	0.43 kg
Dimensions Height	77 mm
Interface Separation Bolt	UNF/UNJF 1/2’’-20 Class 3 A with 25.5 mm engagement length
Interface Separation Nut	Two M5 bolts (or imperial equivalent) placed 52.5 mm apart
Qualification temperature span	-68 to +120 °C
Overall random vibration levels (qualification)	50 gRMS
Release time dispersion	Within 2.0 ms on a 3σ-level
Reliability	0.99995 at a 95% confidence level

Smallest low-shock separation nut of the family, developed to fit OneWeb-class satellites of typically 100-200 kg.

1 12

Target spacecraft class	OneWeb class satellites, typically 100-200 kg
Qualification	AIAA S-113-2005 (former DOD-E-83578A)
Initiators	Dual NSI equivalent (PC23, 103377-191/-449/-500, PD222400024-009, 2-8001140-1, 852420-XX)
Worst-case tests passed	Single 80% initiator, cold case, no internal lube, no o-ring, 150% external load - 100% success
Design feature	Internal mechanical leverage reduces initiator pressure spike and shock; wide thermal operation range
Bolt pretension	25 kN
Mass	0.23 kg
Dimensions	58.5 mm
Interface	UNF/UNJF 3/8’’-24 Class 3 A
Overall random vibration	50 gRMS
Release time dispersion	Within 2.0 ms
Reliability	0.99995 at a 95% confidence level

Flight-proven

Fully qualified high-power Solar Array Drive Mechanism from Beyond Gravity's modular SADM family, qualified for LEO and GEO missions.

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Type	Solar Array Drive Mechanism (high power class)
Qualification	Fully qualified; qualified for LEO and GEO missions
Slip ring	In-house gold-on-gold slip ring technology
Modularity	Interfaces remain the same regardless of power class
Assembly	Actuator part, slip ring with connectors, customizable solar array connectors, motor and sensor connectors, mounting interface
Availability	Rolling stock for short lead times
Max. output speed	1.0 °/s
Lifetime	15 years in orbit
Unpowered holding torque	~7 Nm
Powered Holding Torque	max. 55 Nm
Delivered Output Torque @ 200 mA	> 55 Nm
Delivered Output Torque @ 300 mA	> 55 Nm
Motor Back-EMF Constant	2.33 Vs/rad
Position Output Accuracy	± 1°
Position Output availability	0° … 356.5°
Max. Dead Band	< 3.5°
Potentiometer End-to-End Resistance	10 kΩ ±10%
Operating Voltage	2.5 V .. 12 V
Coil Resistance @ 20°C	76 Ω ± 10%
Coil Inductance @ 20°C	156 mH ± 20%
Motor time constant	2 ms
Max. Outer Diameter mounting flange	144 mm

Flight-proven

Fully qualified Solar Array Drive Mechanism variant of the modular SEPTA family for demanding missions.

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Type	Solar Array Drive Mechanism (high power class, demanding missions)
Qualification	Fully qualified; qualified for LEO and GEO missions
Slip ring	Flight proven in-house slip ring technology
Modularity	Interfaces remain the same regardless of power class
Assembly	Actuator part, slip rings with connectors, customizable solar array connectors, motor and sensor connectors, mounting interface
Availability	Rolling stock for short lead times
Max. output speed	1.0 °/s
Lifetime	15 years in orbit
Unpowered holding torque	~7 Nm
Powered Holding Torque	max. 55 Nm
Delivered Output Torque @ 200 mA	> 55 Nm
Delivered Output Torque @ 300 mA	> 55 Nm
Motor Back-EMF Constant	2.33 Vs/rad
Position Output Accuracy	± 1°
Potentiometer End-to-End Resistance	10 kΩ ±10%
Operating Voltage	2.5 V .. 12 V
Coil Resistance @ 20°C	76 Ω ± 10%
Coil Inductance @ 20°C	156 mH ± 20%
Motor time constant	2 ms
Max. Outer Diameter mounting flange	144 mm
Axial Load	6’670 N
Radial Load	4’890 N
Bending Load	420 Nm
Torsional Load	>56 Nm

Flight-proven

Constellation SADM for small satellites, produced at up to 18 units per month with more than 100 flight models already delivered.

1 7

Target application	Small satellites and constellations
Production rate	Up to 18 units per month
Units delivered	More than 100 flight models
Qualification status	TRL8 completed for all variants; TRL9 by projected launch end of 2025
Power transfer options	One or two gold-on-gold slip rings, or cable wrap
Lead time	Rolling stock for lead times of 12 months
Drive electronics	Proven combinations with SADE drive electronics available

Lightweight modular Ka-band slice converter (30 GHz to 20 GHz) with external LO and EPC configuration for space-constrained payloads.

1 14

Conversion	30 GHz to 20 GHz (Ka-band)
Architecture	External LO and EPC configuration; modular and scalable
Technology	Latest MMIC technologies
Power	Low DC power consumption
Frequency range, Input	27.5 to 31.0 GHz
Frequency range, Output	17.7 to 21.2 GHz
LO Frequency range	7.0 to 12.0 GHz
Gain	28 - 34 dB
Transmit Band Gain	<-20 dB
OIP3	>28 dBm
Noise figure	<15 dB
Operating temperature	-20°C to + 70°C
Mass	0.24 kg
Dimensions	111 x 31 x 71 mm

Flight-proven

Custom and modular space slip rings for solar array drives, payloads and limited-angle actuators, with over 2,000 cumulative years of flight time.

1 6

Product families	SADA/SADM slip rings, payload slip rings, limited angular rotational actuator slip rings
Modular ranges	C-Series cylindrical modules, P-Series planetary modules (stackable)
Power classes	Below 3 kW to above 30 kW
Contact technology	Gold-on-gold
Flight heritage	Over 2,000 cumulative years of flight time; 100% mission success rate
Experience	Over 60 years

Electrical or manual lifting devices for instruments and spacecraft of all sizes, with fixed or convertible hoisting axis and optional CoG adjustment.

1 4

Actuation	Electrical or manual
Hoisting axis	Fixed, or convertible between horizontal and vertical configuration
Options	Remote control for lifting, centre-of-gravity adjustment
Range	From small instruments to very large spacecraft

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