EXA (Astro-und Feinwerktechnik)

Updated 16 Jul 2026

Manufacturer Germany Listed

21 Products

5 Services

33 Years Active

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About EXA (Astro-und Feinwerktechnik)

Astro- und Feinwerktechnik Adlershof GmbH (ASTROFEIN) is a German aerospace manufacturer based in Berlin-Adlershof, officially launched on 12 October 1993 as a spin-off from the German Aerospace Center (DLR). Starting as a five-person precision engineering company, ASTROFEIN has grown into a recognized, certified (DIN EN ISO 9001:2015 and DIN EN 9100:2018) supplier of space components and systems, now employing around 85 people across engineering, manufacturing, and quality assurance.

The company's product portfolio centers on actuators for small-satellite attitude and orbit control systems (AOCS) — including a wide range of reaction wheels from the RW1 up to the RW6000 — as well as ejection mechanisms for CubeSats under the ASTROFEIN PicoSatellite Launcher (PSL) product line, available from PSL1U up to PSL16U. ASTROFEIN is considered one of the world market leaders in reaction wheels and has been described by a customer as "the Ferrari among deployers" for its patented modular launcher design.

Beyond actuators and deployers, ASTROFEIN develops additional AOCS components such as gyro systems, GPS receivers, and magnetometers, along with the ASTROFEIN ACS Test Stand for attitude control system testing and qualification of small satellites and microsatellite buses. The company offers full in-house capability across engineering, manufacturing, and environmental simulation/qualification testing, and has contributed system integration work to missions such as TET and BIROS.

ASTROFEIN's customers and partners include Airbus, DLR, OHB, Jena-Optronik, Spaceflight Inc., and Nanoracks, reflecting its position as an established supplier within the European and international small-satellite supply chain.

Company Info

Headquarters Berlin (Adlershof), Germany, Germany

Founded 1993 (33 years)

Specializations

manufacturer

Website astrofein.com/en ↗

LinkedIn de.linkedin.com/company/astrofein-astro-und-feinwerktechnik-adlershof-gmbh ↗

Email info@astrofein.com

Photos 4

Products

The ASTROFEIN ACM Magnetometer is a high-precision, space-qualified magnetometer designed for attitude control in small and larger satellites, offering an optimal balance of low mass, size, data quality, and power consumption.

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Range	±60 000 nT (up to 140 000 nT on request)
Resolution	100 pT/LSB
Noise	50 pT/ √Hz@60 000 nT
Linearity	0.025%
Mass	< 280 g
Dimensions (without connector)	138 mm x 55 mm x 39 mm
Supply voltage	18 V to 36 V
Power consumption earth field	< 1.0 W @ 24 V
Power consumption full range	< 1.2 W @ 24 V
Data interfaces	RS485 (others on request)
Operation temperature range	-20°C to +50°C
Non-operation temperature range	-30°C to +60°C
Design lifetime	7 years
Storage time	2 years

The ASTROFEIN ACS Test Bed is a comprehensive test stand for verifying the attitude control systems of mini and microsatellites, offering end-to-end testing capabilities including magnetic field, sun, GNSS, and star simulations.

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Rotation around vertical axis	free 360°
Rotation around horizontal axis	20° – 30°
Magnetic field simulation	High-precision in-orbit
Cog calibration	Electronic
Sun simulation	Adjustable and movable
Command interface	WLAN
Power supply	For the test object
GNSS simulator support	GPS, GLONASS, Galileo, Bei-Dou-2, WAAS, EGNOS, MSAS, GAGAN, SDCM, QZSS and IRNSS
Star simulator optical heads	Up to four simultaneously
Star simulator capabilities	Simulates stars, planets, sun, moon, scattered light and protons
Nanosat test bed disturbance torque	Ultra-low
Nanosat test bed CUBESAT compatibility	3U to 16U in different orientations

ARGO-L1 is a configurable, redundant GPS receiver unit designed for LEO missions, offering improved solution availability through a dual independent passive receive antenna system.

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Frequency	GPS L1 Band, C/A code
Number of correlator channels	12
Signal acquisition threshold	35 dB-Hz
Receiver startup mode ttff warm start	< 3 min (90%)
Receiver startup mode ttff cold start	< 15 min (90%)
Timing accuracy (1PPS signal)	< 0.1 us (1 sigma)
Navigation accuracy position	10 m (3D rms)
Navigation accuracy velocity	0.1 m/s (3D rms)
Update rate	1 Hz
Dimensions - receiver unit box configuration 1	130.0 x 216.6 x 34.4 mm3
Dimensions - receiver unit box configuration 2	51.0 x 216.6 x 109.4 mm3
Dimensions - receive antenna diameter	88.9 mm
Dimensions - receive antenna height (incl. connector)	28.7 mm
RF signal lna	44 x 27 x 10.5 mm3
Mass (2x antennas and 2x lnas) configuration 1&2	< 1200 g
Power supply voltage	18 V to 36 V
Power consumption stand alone single receiver	2.2 Wa
Power consumption single receiver with 2x lnas	2.4 Wb
I/o data bus	CAN 2.0 and RS422 (others on request)
Operation temperature range receiver and lna	-20°C to +60°C
Operation temperature range antenna	-55°C to +85°C
Non-operation temperature range receiver and lna	-30°C to +70°C
Design lifetime	7 years in LEO
Storage time	3 years
Total ionization dose	>20 kradc

The ASTROFEIN Gyro System AGS-1 is a tri-axial rotation measurement system designed for small satellites, offering temperature-compensated data and low power consumption.

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Channels	3
Range (per channel)	± 40 °/s
Bias (per channel)	≤ 1 °/h
Noise (random walk per channel)	≤ 0.1 °/ √ h
Measurement frequency	200 Hz
Start-uptime	< 0.3 s
Mass	< 1 kg
Dimensions	134 mm x 85 mm x 60 mm
Supply voltage	18 V to 34 V
Power consumption steady state	8 W
Power consumption maximum	10 W
Data interfaces	RS422 (others on request)
Operation temperature range	-15°C to +40°C
Non-operation temperature range	-30°C to +60°C
Design lifetime	5 years in low earth orbit
Storage time	3 years

Flight-proven

The ASTROFEIN PicoSatellite Launcher (PSL) series offers deployers for 1U, 2U, and 3U CubeSats, featuring a flight-proven non-explosive lock and release mechanism.

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CUBESAT rail length (z)	113.5 (PSL1U), 227.0 (PSL2U), 340.5 (PSL3U)
CUBESAT rail width (x)	100 (PSL1U), 100 (PSL2U), 100 (PSL3U) mm
CUBESAT rail height (y)	100 (PSL1U), 100 (PSL2U), 100 (PSL3U) mm
Number of tuna cans	1 (PSL1U), 1 (PSL2U), 1 (PSL3U)
Maximum satellite mass	<=1.33 (PSL1U), <=2.66 (PSL2U), <=4.0 (PSL3U)

The MicroCMG is a Control Moment Gyroscope designed for small satellites, providing attitude control with high angular momentum and torque capabilities.

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Angular momentum	8.0 Nms
Nominal rotation speed	3820 rpm
Nomial torque	14.0 Nm
Mass	≤ 8.0 kg
Dimensions	188 x 188 x 240 mm³
Operating temperature	-20 °C to +50 °C
Lifetime hardware	11 years

Flight-proven

The ASTROFEIN PSL12U and PSL12U XL are flight-proven CubeSat deployers designed for 1U to 12U CubeSats and combinations, featuring non-explosive lock and release mechanisms and very low power consumption.

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Parameter	PSL12U
CUBESAT rail length (z)	340.5 mm
CUBESAT rail width (x)	226.3 mm
CUBESAT rail height (y)	226.3 mm
Number of tuna cans	5*
Maximum satellite mass	<=24.0 kg
Parameter (2)	PSL12U XL
CUBESAT rail length (z) (2)	366 -0.5/+5.0 mm
CUBESAT rail width (x) (2)	226.3 mm
CUBESAT rail height (y) (2)	226.3 mm
Number of tuna cans (2)	5*
Maximum satellite mass (2)	<=24.0 kg

The ASTROFEIN PSL6U and PSL6U XL are CubeSat deployers designed for 1U, 2U, 3U, or 6U CubeSats, featuring non-explosive mechanisms and a user-friendly, resettable system.

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Parameter	PSL6U
CUBESAT rail length (z)	340.5 mm
CUBESAT rail width (x)	226.3 mm
CUBESAT rail height (y)	100 mm
Number of tuna cans	2
Maximum satellite mass	<=12.0 kg
Parameter (2)	PSL6U XL
CUBESAT rail length (z) (2)	366 -0.5/+5.0 mm
CUBESAT rail width (x) (2)	226.3 mm
CUBESAT rail height (y) (2)	100 mm
Number of tuna cans (2)	2
Maximum satellite mass (2)	<=12.0 kg

The RW1 is a reaction wheel designed for small satellites, featuring separate wheel drive electronics and available with two different rotating masses (Type A or Type B) to provide precise attitude control.

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Parameter	Type A
Angular momentum	5.8 E-4 Nms
Nominal rotation speed	8000 rpm
Maximum rotation speed	≈ 16 380 rpm
Speed resolution	0.25 rpm (1LSB)
Nomial torque (max. commandable)	23 E-6Nm
Torque deviation – rms value	<2.2 E-6Nm
Supply voltage	5 V
Power consumption for wde1 (stand by, motor off, pwde) wde for 1 wheel	< 250 mW
Power consumption for wde1 (stand by, motor off, pwde) wde for 3 wheels	< 350 mW
Power consumption for wde1 (stand by, motor off, pwde) wde for 4 wheels	< 500 mW
Maintaining nominal rotation speed1,2	< 275 mW + PWDE
Maximum consumption1,2	< 375 mW + PWDE
Mass (including 40 cm cable)	≤ 24 g
Wde mass	≤ 45 g
Moment of inertia	694.5 E-9 kg m2
Dimension single wheel	21 x 12 x 21 mm3
Temperature operation	-20 °C to +50 °C
Temperature non-operation	-40 °C to +65 °C
Design lifetime	1 year in LEO
Storage time	2 years including 250h of ground operation
Parameter (typ)	Type B
Angular momentum (2)	1.0 E-4 Nms
Nomial torque (max. commandable) (2)	4 E-6Nm
Torque deviation – rms value (2)	0.8 E-6Nm
Maintaining nominal rotation speed1,2 (2)	< 200 mW + PWDE
Maximum consumption1,2 (2)	< 300 mW + PWDE
Mass (including 40 cm cable) (2)	≤ 15 g
Moment of inertia (2)	119.5 E-9 kg m2
Dimension single wheel (2)	21 x 12 x 21 mm3

The RW100 is a reaction wheel for small satellites, optimized for constellation applications and based on the RW90 design.

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Angular momentum	0.4 Nms @ nominal speed
Nominal rotation speed	6000 rpm
Nomial reaction torque	0.02 Nm Max. commandable deliverable output torque over the whole speed range
Supply voltage	18 to 34 V
Power consumption	≤ 2 W Stand by (motor off)
Power consumption (2)	≤ 5.0 W @ 6000 rpm
Power consumption (max)	20 W Maximum (max. torque/max. speed)
Mass	≤ 0.8 kg
Moment of inertia	6.52x10-4 kg m2 Rotating mass
Dimensions	100 mm x 100 mm x 60 mm
Operation	-20 °C to +60 °C
Start-up	-30 °C to +70 °C
Survival temperature	-40 °C to +75 °C
Data interface	RS485/RS422
Design lifetime	> 7 years In LEO
Storage time	> 3 years (incl. 240 h of ground operation)

The RW150 is a reaction wheel designed for small satellites, featuring integrated wheel drive electronics, various operation modes, and high torque and speed stability.

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Angular momentum	1.0 Nms
Nominal rotation speed	6000 rpm
Nomial reaction torque	0.03 Nm
Supply voltage	18 to 34 V
Power consumption stand by (motor off)	≤ 2 W
Power consumption @ 1500 rpm	≤ 5.0 W
Power consumption @ 6000 rpm	≤ 10 W
Power consumption maximum (max. torque/max. speed)	42 W
Mass	≤ 1.3 kg
Moment of inertia	1.592x10-3 kg m2
Dimensions	150 mm x 150 mm x 60 mm
Operation temperature	-20 °C to +50 °C
Start-up temperature	-30 °C to +55 °C
Survival temperature	-40 °C to +60 °C
Data interface	RS485/RS422
Design lifetime	> 7 years In LEO
Storage time	> 3 years (incl. 240 h of ground operation)

The RW1500 is a reaction wheel currently under development, designed for satellite attitude control with an angular momentum of 25.0 Nms and a nominal rotation speed of 4000 rpm.

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Angular momentum	25.0 Nms @ nominal speed
Nominal rotation speed	4000 rpm
Nomial reaction torque	0.2 Nm Max. commandable reaction torque
Supply voltage	22 to 37 V
Power consumption	≤ 2.5 W Stand by (motor off)
Power consumption (max)	≤ 30.0 W @ nominal speed 0.1 Nm/max speed
Power consumption (max) (max)	≤ 140 W Maximum (0.2 Nm/max. speed)
Mass	≤ 6.0 kg
Moment of inertia	5.97e-2 kg m2 Rotating mass
Dimensions	320 x 320 x 120 mm3
Operation	-20 °C to +60 °C
Start-up	-30 °C to +60 °C
Survival temperature	-40 °C to +65 °C
Data interface	CAN/RS485
Design lifetime	> 15.5 years
Storage time	> 6 years including 1500h of ground operation

The RW25 is a compact reaction wheel designed for nano-satellite applications, featuring integrated electronics for independent operation via a digital interface.

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Angular momentum	30 mNms
Nominal rotation speed	5000 rpm
Nomial torque (max. commandable)	2 mNm (more by design possible)
Communication	SPI preferred (CAN possible)
Supply voltage	5 V
Maintaining nominal rotation speed	< 1.5 W
Maximum consumption (max. torque @ max. speed)	< 2.8 W
Mass	200 g
Dimension single wheel	50 mm x 50 mm x 25.5 mm
Operation	-20 °C to +50 °C
Non-operation	-40 °C to +65 °C
Storage time	2 years (includes up to 240 hours of ground operations)
Design change flexibility without radical design change (mass, power may change)	Increased/decreased angular momentum and torque possible

The RW250 is a reaction wheel for small satellites, featuring integrated wheel drive electronics, various operation modes, and extensive housekeeping data.

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Angular momentum	4.0 Nms @ nominal speed
Nominal rotation speed	5000 rpm
Nomial reaction torque	0.1 Nm Max. commandable deliverable output torque over the whole speed range
Supply voltage	23 to 34 V
Power consumption	≤ 2.5 W Stand by (motor off)
Power consumption (2)	≤ 7.0 W @ 1500 rpm
Power consumption (3)	≤ 13 W @ 5000 rpm
Power consumption (max)	100 W Maximum (max. torque/max. speed)
Mass	≤ 2.7 kg
Moment of inertia	7.65x10-3 kg m2 Rotating mass
Dimensions	Height: 81.6 mm Diameter: 180 mm
Operation	-20 °C to +50 °C
Start-up	-30 °C to +60 °C
Survival temperature	-40 °C to +70 °C
Data interface	RS485/RS422
Design lifetime	> 7 years In LEO
Storage time	> 3 years (incl. 240 h of ground operation)

The RW3000 is a reaction wheel designed for satellite attitude control, currently under development. It offers an angular momentum of 50 Nms and a nominal reaction torque of 0.2 Nm.

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Angular momentum	50.0 Nms @ nominal speed
Nominal rotation speed	4000 rpm
Nomial reaction torque	0.2 Nm Max. commandable reaction torque
Supply voltage	22 to 37 V
Power consumption	≤ 2.5 W Stand by (motor off)
Power consumption (max)	≤ 30.0 W @ nominal speed 0.1 Nm/max speed
Power consumption (max) (max)	≤ 75 W Maximum (0.2 Nm/max. speed)
Power consumption (max) (max)	≤ 140 W Maximum (0.2 Nm/max. speed)
Mass	≤ 9.0 kg
Moment of inertia	1.19e-1 kg m2 Rotating mass
Dimensions	370 x 370 x 120 mm3
Operation	-20 °C to +60 °C
Start-up	-30 °C to +60 °C
Survival temperature	-40 °C to +65 °C
Data interface	CAN/RS485
Design lifetime	> 15.5 years
Storage time	> 6 years including 1500h of ground operation

The RW35 is a reaction wheel designed for small satellites, featuring integrated drive electronics, high torque and speed stability, and extensive housekeeping capabilities.

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Angular momentum	0.1 Nms
Nominal rotation speed	5000 rpm
Nomial torque (max. commandable)	0.005 Nm
Moment of inertia (rotating mass)	1.9 x 10-4 kgm2
Supply voltage	18 V - 34 V
Stand by (motor off)	≤ 2.0 W
Conservation of rotation speed1	≤ 4 W @ nominal rotation speed
Max. acceleration1	≤ 9 W
Mass	< 0.5 kg
Dimension single wheel with flange	102 x 102 x 58 mm³
Operation	-20 °C to +50 °C
Non-operation	-30 °C to +60 °C
Storage	-40°C to +65°C
Radiation (total dose)	20 krad (behind 2 mm Al-Shield) in LEO
Data interface	RS-422 (RS-485 optional)
Design lifetime	5 years
Storage time	3 years (includes up to 240 hours of ground operations)

The RW6000 is a large reaction wheel currently under development by ASTROFEIN, designed for satellite attitude control with high angular momentum and reaction torque capabilities.

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Angular momentum	100.0 Nms @ nominal speed
Nominal rotation speed	4200 rpm
Nomial reaction torque	0.2 Nm Max. commandable reaction torque
Supply voltage	23 to 34 V
Power consumption	≤ 5.0 W Stand by (motor off)
Power consumption (min)	≤ 30.0 W @ nominal speed
Power consumption (max)	≤ 75 W 0.1 Nm/max. speed
Power consumption (max) (max)	≤ 150 W Maximum (0.2 Nm/max. speed)
Mass	≤ 12.5 kg
Moment of inertia	2.274e-1 kg m2 Rotating mass
Dimensions	446 x 442 x 149 mm3
Operation	0 °C to +60 °C
Start-up	0 °C to +60 °C
Survival temperature	0 °C to +65 °C
Data interface	CAN
Design lifetime	> 15.5 years
Storage time	> 6 years including 1500h of ground operation

The RW800 is a reaction wheel for satellites, currently under development with an engineering model available, designed for attitude control.

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Angular momentum	12.0 Nms
Remark	@ nominal speed
Nominal rotation speed	3600 rpm
Nomial reaction torque	0.2 Nm
Remark (max)	Max. commandable reaction torque
Supply voltage	23 to 34 V
Power consumption	≤ 2.5 W
Remark (3)	Stand by (motor off)
Power consumption (2)	≤ 25.0 W
Remark (min)	@ nominal speed
Power consumption (3)	≤ 70 W
Remark (max) (max)	0.1 Nm/max. speed
Power consumption (4)	≤ 140 W
Remark (max) (max)	Maximum (0.2 Nm/max. speed)
Mass	≤ 6.0 kg
Moment of inertia	3.183e-2 kg m2
Remark (7)	Rotating mass
Dimensions	250 x 250 x 100 mm3
Operation	-20 °C to +60 °C
Start-up	-25 °C to +60 °C
Survival temperature	-30 °C to +65 °C
Data interface	CAN/RS485
Design lifetime	> 15.5 years
Storage time	> 6 years
Remark (8)	including 1500h of ground operation

The RW90 is a reaction wheel designed for small satellites, featuring integrated drive electronics, multiple operation modes, and high torque and speed stability.

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Angular momentum	0.35 Nms @7800 rpm
Nominal rotation speed	6000 rpm
Nomial reaction torque	0.015 Nm Max. commandable deliverable output torque over the whole speed range
Power consumption	≤ 1.8 W Stand by (motor off)
Power consumption (2)	≤ 2.7 W @ 3000 rpm
Power consumption (3)	≤ 3.5 W @ 6000 rpm
Power consumption (max)	15 W Maximum (max. torque/max. speed)
Moment of inertia	4.35 x10-4 kgm2 Rotating mass
Dimensions	100 mm x 100 mm x 60 mm
Operation	-30 °C to +60 °C
Start-up	-30 °C to +60 °C
Survival temperature	-40 °C to +65 °C
Data interface	RS485/RS422
Design lifetime	> 7 years In LEO
Storage time	> 3 years (incl. 240 h of ground operation)

The RWT250 is a reaction wheel designed for small satellites, featuring integrated wheel drive electronics, various operation modes, and extensive housekeeping data.

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Angular momentum	4.0 Nms @ nominal speed
Nominal rotation speed	5000 rpm
Nomial reaction torque	0.3 Nm Max. commandable deliverable output torque over the whole speed range
Supply voltage	23 to 34 V
Power consumption	≤ 3.0 W Stand by (motor off)
Power consumption (2)	≤ 15.0 W @ 5000 rpm
Power consumption (max)	≤ 200 W Maximum (max. torque/max. speed)
Mass	≤ 3.0 kg
Moment of inertia	7.64e-3 kg m2 Rotating mass
Dimensions	Height: ≈100 mm Diameter: 200 mm
Operation temperature	-20 °C to +50 °C
Start-up temperature	-30 °C to +60 °C
Survival temperature	-30 °C to +70 °C
Data interface	RS485/CAN
Design lifetime	> 7 years (Depending on electronics grade (up to 10 years))
Storage time	> 3 years (incl. 240 h of ground operation)

The RWT150 is an upscaled reaction wheel for small satellites, currently under development, designed to provide attitude control with a nominal angular momentum of 1.0 Nms.

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Angular momentum	1.0 Nms @ nominal speed
Nominal rotation speed	6000 rpm
Nomial reaction torque	0.1 Nm Max. commandable deliverable output torque over the whole speed range
Supply voltage	18 to 34 V
Power consumption	≤ 2.5 W Stand by (motor off)
Power consumption (2)	≤ 7 W @ steady state
Power consumption (max)	< 60 W Maximum (max. torque/max. speed)
Mass	≤ 1.3 kg
Dimensions	150 mm x 150 mm x 60 mm
Operation	-20 °C to +50 °C
Start-up	-30 °C to +60 °C
Survival temperature	-40 °C to +70 °C
Data interface	RS485/RS422
Design lifetime	> 7 years In LEO
Storage time	> 3 years (incl. 240 h of ground operation)

Additional Services

Engineering & analysis

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ASTROFEIN offers a wide range of engineering services for aerospace projects, covering design, system, software, electrical, thermal, and structural aspects. Their experienced team advises on processes, methods, and tool usage throughout the project lifecycle. They specialize in space engineering for…

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ASTROFEIN's Design Engineering focuses on space components for satellites, probes, and landers. Their engineers develop and design parts, components, and devices for industry and research, from prototype development to flight patterns. They are proficient in calculating static and dynamic strengths…

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ASTROFEIN's software team is responsible for developing firmware for the embedded systems within their products. This includes programming microcontrollers and FPGAs for electronic components, as well as developing support tools. Their experienced engineers create concepts and specifications in close cooperation…

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ASTROFEIN's system engineers are responsible for the technical coordination of the development of satellite components and subsystems, with a particular focus on attitude control, structure, and mechanisms. They manage the entire development cycle, from defining requirements and overseeing the design…

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ASTROFEIN's specialists in finite element method (FEM) and FEM structural analysis simulate and test various physical relationships. Their focus includes complex calculations such as linear statics, non-linear analysis, dynamic frequency and natural frequency analysis, harmonic analysis, and PSD analysis. Thermal…

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EXA (Astro-und Feinwerktechnik)

About EXA (Astro-und Feinwerktechnik)

Photos 4

Products

ASTROFEIN ACM Magnetometer

ASTROFEIN ACM Magnetometer

Description

Specifications

ASTROFEIN ACS Test Bed

ASTROFEIN ACS Test Bed

Description

Specifications

ASTROFEIN GPS receiver unit- ARGO

ASTROFEIN GPS receiver unit- ARGO

Description

Specifications

ASTROFEIN Gyro System AGS-1

ASTROFEIN Gyro System AGS-1

Description

Specifications

ASTROFEIN PicoSatellite Launcher PSL1U / PSL2U / PSL3U

ASTROFEIN PicoSatellite Launcher PSL1U / PSL2U / PSL3U

Description

Specifications

MicroCMG

MicroCMG

Description

Specifications

PicoSatellite Launcher PSL12U / PSL12U XL

PicoSatellite Launcher PSL12U / PSL12U XL

Description

Specifications

PicoSatellite Launcher PSL6U / PSL6U XL

PicoSatellite Launcher PSL6U / PSL6U XL

Description

Specifications

Reaction Wheel RW1

Reaction Wheel RW1

Description

Specifications

Reaction Wheel RW100

Reaction Wheel RW100

Description

Specifications

Reaction Wheel RW150

Reaction Wheel RW150

Description

Specifications

Reaction Wheel RW1500

Reaction Wheel RW1500

Description

Specifications

Reaction Wheel RW25

Reaction Wheel RW25

Description

Specifications

Reaction Wheel RW250

Reaction Wheel RW250

Description

Specifications

Reaction Wheel RW3000

Reaction Wheel RW3000

Description

Specifications

Reaction Wheel RW35

Reaction Wheel RW35

Description

Specifications

Reaction Wheel RW6000

Reaction Wheel RW6000

Description

Specifications

Reaction Wheel RW800

Reaction Wheel RW800

Description

Specifications

Reaction Wheel RW90

Reaction Wheel RW90

Description

Specifications