AAC Clyde Space

Manufacturer Sweden Verified

48 Products

27 Years Active

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About AAC Clyde Space

AAC Clyde Space is a publicly listed (Nasdaq First North) Swedish-UK small satellite company formed through the merger of AAC Microtec (Sweden) and Clyde Space (Scotland). The company designs and manufactures CubeSat platforms (1U to 16U), electrical power systems, attitude control systems, and radios for nanosatellites. AAC Clyde Space provides end-to-end mission services and operates its own satellite constellation for Earth observation data.

Milestones

1999 AAC Microtec founded in Sweden
2005 Clyde Space founded in Glasgow
2019 Merger creating AAC Clyde Space

Company Info

Headquarters Uppsala, Sweden (also Glasgow, UK), Sweden

Founded 1999 (27 years)

Specializations

satellite manufacturing earth observation

Website aac-clyde.space ↗

Products

TRL 8 · Qualified

S-band antenna controller for small satellites, managing antenna deployment and orientation for reliable communication links.

1 8

Frequency Band	S-band
Interface	RS-422 / I2C
Power Consumption	~2 W
Operating Temperature	-40°C to +85°C
Mass	~80 g
Dimensions	~90 x 90 x 15 mm
TRL Level	8
Compatibility	SpaceQuest TRX-U, third-party S-band antennas

TRL 9 · Flight-proven

Deployable UHF/VHF antenna system for CubeSats enabling ground station communication in amateur frequency bands.

1 7

Frequency Bands	UHF (400-450 MHz), VHF (130-175 MHz)
Deployment Mechanism	Burn-wire / shape-memory alloy
Interface	I2C
Power (deployment)	~1.5 W
Mass	~35 g
Stowed Dimensions	~90 x 90 x 6 mm
TRL Level	9

TRL 9 · Flight-proven

Miniature GPS patch antenna for CubeSats providing L1 band reception for on-orbit navigation and orbit determination.

2 24

Frequency	1575.42 MHz (GPS L1)
Antenna Type	Patch antenna with LNA
Gain	>25 dBic
Noise Figure	<1.5 dB
Interface	SMA connector
Supply Voltage	3.3 V
Power Consumption	<40 mA
Operating Temperature	-40°C to +85°C
Mass	~15 g
Dimensions	25 x 25 x 8 mm
Radiation Tolerance	10 KRad
TRL Level	9
Axial Ratio	<3 dB (at zenith)
VSWR	<2:1
Polarization	RHCP
Bandwidth	10 MHz (3 dB)
Mounting	Bolt or adhesive
Compatible Receivers	GNSS-701, uBlox, NovAtel
Coax Cable	Optional (various lengths)
Ground Plane Required	No (integrated)
ESD Protection	Yes
Connector Type	SMA Female
Storage Temperature	-55°C to +125°C
Vacuum Compatible	Yes

TRL 8 · Qualified

A compact, high-resolution multispectral camera payload for CubeSats providing 85cm ground sample distance (GSD) Earth observation imagery.

2 17

Ground Sample Distance (GSD)	85 cm at 500 km SSO
Spectral Bands	Panchromatic, Red, Green, Blue, NIR
Swath Width	~4.3 km at 500 km
Image Sensor	CMOS
Mass	~400 g
Power Consumption	~5 W (operating)
Interface	SpaceWire / LVDS
Operating Temperature	-10°C to +50°C
Storage Temperature	-30°C to +70°C
Radiation Tolerance	10 KRad
TRL Level	8
Dimensions	~100 x 100 x 150 mm
Data Output	Compressed image files (JPEG2000)
Frame Rate	Up to 4 fps
Onboard Storage	16 GB
Focal Length	400 mm
Aperture	f/4.5

TRL 8 · Qualified

S-band communications system for CubeSats enabling high-rate downlink for Earth observation and other data-intensive satellite missions.

2 15

TX Frequency	2200-2290 MHz (S-band downlink)
RX Frequency	2025-2120 MHz (S-band uplink)
TX Output Power	Up to 1 W
Data Rate (downlink)	Up to 4 Mbps
Modulation	BPSK, QPSK
Interface	RS-422 / SpaceWire
Supply Voltage	5 V
Power Consumption (TX)	~6 W
Power Consumption (RX)	~1 W
Operating Temperature	-20°C to +60°C
Mass	~180 g
Dimensions	~100 x 100 x 20 mm
Radiation Tolerance	10 KRad
TRL Level	8
Protocol Support	CCSDS framing

Flight-proven electrical power system for 3U-16U CubeSats featuring Maximum Power Point Tracking and robust reliability with TRL 9 maturity.

1 22

Design Life	5 years in LEO
Regulated Power Buses	3.3V; 5V; and 12V
Latching Current Limit (LCL)	10 Configurable
Interfaces	I2C
Max. Battery Voltage	8.2V
Operating Temperature	-40°C to 85°C
Storage Temperature	-50°C to 100°C
Vacuum	10⁻⁵ torr
Radiation Tolerance	10 KRad
Vibration	To [RD-3]
NANO - Intended Use	2U and 3U CubeSat with body panels
NANO - Mass (typical)	86 g
NANO - Length	95.89 mm
NANO - Width	90.17 mm
NANO - Height	16.2 mm
NANO-PLUS - Intended Use	3-12U CubeSat with deployable panels
NANO-PLUS - Mass (typical)	148 g
NANO-PLUS - Length	95.89 mm
NANO-PLUS - Width	90.17 mm
NANO-PLUS - Height	20.82 mm
NANO - Integrated Battery	No
NANO-PLUS - Integrated Battery	No

TRL 7 · Demonstrated

A miniaturized Fourier Transform spectrometer for CubeSats enabling atmospheric and surface composition analysis from orbit.

1 14

Spectral Range	1400-1700 nm (configurable)
Spectral Resolution	< 1 nm
Instrument Type	Fourier Transform (Michelson interferometer)
Mass	~600 g
Power Consumption	~8 W (operating)
Interface	USB / SpaceWire
Operating Temperature	-10°C to +40°C
Radiation Tolerance	10 KRad
TRL Level	7
Dimensions	~100 x 100 x 200 mm
Signal-to-Noise Ratio	>1000:1
Data Rate	1 Mbps
Field of View	< 1°
Detector Type	InGaAs photodetector array

TRL 7 · Demonstrated

High-speed gigabit optical detector for small satellites enabling fast inter-satellite or satellite-to-ground optical communication links.

1 29

Data Rate	Up to 1 Gbps
Detector Type	Avalanche Photodiode (APD)
Wavelength Range	800-1600 nm
Sensitivity (min)	-35 dBm
Bandwidth	>1 GHz
Interface	SpaceWire / LVDS
Supply Voltage	3.3 V / 5 V
Power Consumption	~3 W
Operating Temperature	-40°C to +85°C
Storage Temperature	-55°C to +100°C
Mass	~120 g
Dimensions	~90 x 90 x 20 mm
Radiation Tolerance	10 KRad
TRL Level	7
Bit Error Rate (BER)	<10⁻⁹
Field of View (RX)	Configurable (depends on optics)
Optical Connector	FC/APC or SMA (fiber)
Clock Recovery	Integrated CDR
Output Format	NRZ serial data
APD Bias Voltage	20-100 V (auto-controlled)
Gain Control	Automatic (AGC)
Dark Current	<10 nA at operating bias
Responsivity	>0.8 A/W at 1064 nm
Eye Diagram Compliance	IEEE 802.3ae
ESD Protection	Yes
Vacuum Compatible	Yes
Outgassing Compliance	ECSS-Q-70-02
Shock Tolerance	500 g, 0.5 ms
Vibration Qualification	ECSS-E-10-03

TRL 9 · Flight-proven

Space-grade multi-constellation GNSS receiver for CubeSats providing precise orbit determination for GPS, GLONASS, and Galileo signals.

1 24

Supported Constellations	GPS L1, GLONASS L1, Galileo E1
Position Accuracy (CEP)	<5 m (GPS L1)
Velocity Accuracy	<0.1 m/s
Time Accuracy	<100 ns
Channels	72 channels
Update Rate	1 Hz (up to 10 Hz)
Acquisition Time (cold)	<60 s
Interface	RS-232, I2C, 1PPS
Supply Voltage	3.3 V
Power Consumption	<1 W
Operating Temperature	-40°C to +85°C
Storage Temperature	-55°C to +125°C
Mass	~40 g
Dimensions	~90 x 90 x 15 mm
Radiation Tolerance	10 KRad
TRL Level	9
Altitude Limit	No software limit (LEO/MEO qualified)
Velocity Limit	No software limit
ITAR Status	EAR99
Flight Heritage	>20 missions
Antenna Interface	SMA (for ANT-GPS or compatible)
Output Protocol	NMEA 0183 / proprietary binary
Anti-jamming	Basic RF filtering
Startup Mode	Cold / warm / hot start

TRL 9 · Flight-proven

Integrated Attitude Determination and Control System for 1U-3U CubeSats, combining sensors and actuators in a single compact board.

1 15

Pointing Accuracy	~1° (3σ)
Attitude Rate	<0.5°/s
Sensors	3-axis magnetometer, sun sensors, gyroscope
Actuators	3-axis magnetorquers
Interface	I2C / CAN
Supply Voltage	3.3 V / 5 V
Power Consumption	~1.5 W
Operating Temperature	-40°C to +85°C
Mass	~90 g
Dimensions	~90 x 90 x 16 mm
Radiation Tolerance	10 KRad
TRL Level	9
Compatible CubeSat Size	1U to 3U
Orbit Support	LEO
ADCS Software	Embedded (EKF-based)

TRL 8 · Qualified

Advanced integrated ADCS for 3U-16U CubeSats with reaction wheels, providing precision pointing for Earth observation and high-demand missions.

2 15

Pointing Accuracy	<0.1° (3σ) with star tracker
Attitude Rate	<0.05°/s
Sensors	3-axis magnetometer, sun sensors, gyroscope, star tracker interface
Actuators	3-axis reaction wheels + magnetorquers
Reaction Wheel Speed	Up to 6000 RPM
Interface	I2C / CAN / SpaceWire
Supply Voltage	5 V / 12 V
Power Consumption	~5 W (peak, all actuators)
Operating Temperature	-40°C to +85°C
Mass	~400 g
Dimensions	~90 x 90 x 50 mm
Radiation Tolerance	10 KRad
TRL Level	8
Compatible CubeSat Size	3U to 16U
ADCS Software	Embedded (EKF/UKF-based)

TRL 7 · Demonstrated

A compact infrared multispectral imager for CubeSats providing thermal and near-infrared imaging capabilities for Earth observation missions.

2 17

Spectral Bands	NIR (0.85 µm), SWIR (1.6 µm), LWIR (10-12 µm)
Ground Sample Distance (GSD)	200 m at 500 km
Swath Width	~40 km at 500 km
Detector Type	InGaAs / microbolometer
Mass	~200 g
Power Consumption	~4 W (operating)
Interface	SpaceWire / LVDS
Operating Temperature	-20°C to +50°C
Storage Temperature	-30°C to +70°C
Radiation Tolerance	10 KRad
TRL Level	7
Dimensions	~100 x 100 x 80 mm
Calibration	Onboard blackbody calibration source
Frame Rate	Up to 25 fps
Onboard Storage	8 GB
NEDT (thermal)	< 100 mK
Focal Plane Cooling	Passive (thermoelectric optional)

Flight-proven CubeSat OBC with ARM Cortex-M3 (SmartFusion2, 62.5 DMIPS at 50 MHz), EDAC, 16 MB MRAM, under 1W power. PLUS variant adds GPS. 5-year LEO design life.

1 16

Design Life	5 years in LEO
Processor	SmartFusion2 SoC ARM Cortex-M3, 62.5 DMIPS
Clock	50 MHz
MRAM	16 MB
Radiation (TiD)	20 kRAD
Nominal Power	400 mW typ, 1 W max
Operating Temperature	-40 to +80 C
I2C	2
SPI	7 Chip Select Lines
UART	8
RS422	1
CAN	1
GPIO	17
Mass	61.9 g
Dimensions	95.89 x 90.17 x 5.51 mm
GPS (PLUS model)	<10m RMS position, <1m/s RMS velocity

TRL 9 · Flight-proven

3-axis magnetometer for CubeSats used for attitude determination and magnetic field mapping in LEO.

2 21

Axes	3
Measurement Range	±100 µT
Resolution	0.1 nT
Accuracy	<2 nT (after calibration)
Noise Density	<0.1 nT/√Hz
Interface	I2C
Supply Voltage	3.3 V
Power Consumption	<50 mW
Operating Temperature	-40°C to +85°C
Storage Temperature	-55°C to +125°C
Mass	~20 g
Dimensions	~90 x 90 x 8 mm
Radiation Tolerance	10 KRad
TRL Level	9
Sampling Rate	Up to 100 Hz
Output Format	16-bit digital
Calibration	Factory calibrated, in-orbit calibration supported
Offset Drift	<10 nT/°C
Cross-axis Sensitivity	<0.5%
Shock Tolerance	1000 g
Vacuum Compatible	Yes

Miniature magnetometer for CubeSats providing 3-axis magnetic field measurements for attitude determination and magnetorquer feedback.

1 9

Axes	3
Measurement Range	±100 µT
Resolution	0.05 nT
Noise Density	<0.05 nT/√Hz
Interface	I2C
Supply Voltage	3.3 V
Power Consumption	<20 mW
Operating Temperature	-40°C to +85°C
Mass	~10 g

TRL 9 · Flight-proven

High-torque 3-axis magnetorquer system for small satellites providing magnetic attitude actuation for detumbling, attitude control, and momentum management.

2 19

Configuration	3-axis (X, Y, Z)
Dipole Moment (each axis)	0.2 A·m²
Max Current	0.5 A
Coil Resistance	~22 Ω
Interface	I2C / Analog PWM
Supply Voltage	5 V
Power Consumption (max)	~3 W (all axes, full torque)
Operating Temperature	-40°C to +85°C
Mass	~140 g
Dimensions	~100 x 100 x 22 mm (main board)
Radiation Tolerance	10 KRad
TRL Level	9
Core Type	Air-core or ferromagnetic (configurable)
Linearity	>99%
Hysteresis	<1%
PWM Frequency	1-10 kHz
Current Accuracy	<1%
EMI Shielding	Optional
Mounting	PCB-stack or panel-mount

TRL 9 · Flight-proven

30 Wh CubeSat battery module for 1U-3U missions featuring space-grade lithium-ion cells with passive thermal management and TRL 9 flight heritage.

2 23

Capacity	30 Wh
Nominal Voltage	8.2 V
Chemistry	Lithium-ion
Design Life	2+ years in LEO
Operating Temperature	-10°C to 45°C (charging), -20°C to 60°C (discharging)
Storage Temperature	-30°C to 70°C
Radiation Tolerance	10 KRad
Vacuum Compatible	Yes
Form Factor	0.5U CubeSat
Mass	195 g
Length	95.89 mm
Width	90.17 mm
Height	27.3 mm
Cell Configuration	2S2P
Max Charge Rate	1C
Max Discharge Rate	2C
Cycle Life	>500 cycles at 80% DoD
Protection	Over-voltage, over-current, over-temperature
Interface	I2C telemetry
TRL Level	9
ISS Compatible	Yes
Heater	Optional
Integrated Heater	Optional add-on

TRL 9 · Flight-proven

40 Wh CubeSat battery module for 3U-6U missions with space-grade lithium-ion cells, passive thermal control, and flight-proven reliability.

2 23

Capacity	40 Wh
Nominal Voltage	8.2 V
Chemistry	Lithium-ion
Design Life	2+ years in LEO
Operating Temperature	-10°C to 45°C (charging), -20°C to 60°C (discharging)
Storage Temperature	-30°C to 70°C
Radiation Tolerance	10 KRad
Vacuum Compatible	Yes
Form Factor	0.5U CubeSat
Mass	255 g
Length	95.89 mm
Width	90.17 mm
Height	27.3 mm
Cell Configuration	2S3P
Max Charge Rate	1C
Max Discharge Rate	2C
Cycle Life	>500 cycles at 80% DoD
Protection	Over-voltage, over-current, over-temperature
Interface	I2C telemetry
TRL Level	9
ISS Compatible	Yes
Heater	Optional
Integrated Heater	Optional add-on

TRL 9 · Flight-proven

80 Wh high-capacity CubeSat battery for 6U-16U missions, providing double the energy storage with the same proven space-grade lithium-ion technology.

2 23

Capacity	80 Wh
Nominal Voltage	8.2 V
Chemistry	Lithium-ion
Design Life	2+ years in LEO
Operating Temperature	-10°C to 45°C (charging), -20°C to 60°C (discharging)
Storage Temperature	-30°C to 70°C
Radiation Tolerance	10 KRad
Vacuum Compatible	Yes
Form Factor	1U CubeSat
Mass	480 g
Length	95.89 mm
Width	90.17 mm
Height	54.6 mm
Cell Configuration	2S6P
Max Charge Rate	1C
Max Discharge Rate	2C
Cycle Life	>500 cycles at 80% DoD
Protection	Over-voltage, over-current, over-temperature
Interface	I2C telemetry
TRL Level	9
ISS Compatible	Yes
Heater	Optional
Integrated Heater	Optional add-on

TRL 8 · Qualified

Precision 3-axis MEMS gyroscope for CubeSats providing high-accuracy angular rate sensing for attitude determination and control.

1 14

Axes	3
Angular Rate Range	±300°/s
Bias Stability (ARW)	<0.05°/√h
Noise Density	<0.003°/s/√Hz
Bias Drift (1σ)	<0.5°/h
Interface	SPI / I2C
Supply Voltage	3.3 V
Power Consumption	<50 mW
Operating Temperature	-40°C to +85°C
Mass	~30 g
Dimensions	~50 x 50 x 12 mm
Radiation Tolerance	10 KRad
TRL Level	8
Output Rate	Up to 2 kHz

TRL 9 · Flight-proven

Double-deployable solar array for CubeSats with two wing panels that fold out on orbit to substantially increase power generation for larger or higher-power missions.

3 12

Solar Cell Type	Triple Junction GaAs
Cell Efficiency	29.5% (BOL)
Panel Type	Double-Deployable
Compatible CubeSat Size	6U to 16U
Operating Temperature	-40°C to +100°C
Radiation Tolerance	10 KRad
TRL Level	9
Interface	I2C (via EPS)
Deployment Mechanism	Spring-loaded passive deployment
Connector	Flexible PCB harness
Coating	Anti-reflective
Vacuum Compatible	Yes

TRL 9 · Flight-proven

Single-deployable solar array panel for CubeSats, folding out from the satellite body to increase power generation area beyond body-mounted options.

3 12

Solar Cell Type	Triple Junction GaAs
Cell Efficiency	29.5% (BOL)
Panel Type	Single-Deployable
Compatible CubeSat Size	3U to 12U
Operating Temperature	-40°C to +100°C
Radiation Tolerance	10 KRad
TRL Level	9
Interface	I2C (via EPS)
Deployment Mechanism	Spring-loaded passive deployment
Connector	Flexible PCB harness
Coating	Anti-reflective
Vacuum Compatible	Yes

TRL 9 · Flight-proven

Body-mounted CubeSat solar panel for 1U to 6U satellites, providing power from a single side-panel with high-efficiency triple junction solar cells.

3 12

Solar Cell Type	Triple Junction GaAs
Cell Efficiency	29.5% (BOL)
Panel Type	Body-mounted (side panel)
Compatible CubeSat Size	1U to 6U
Operating Temperature	-40°C to +100°C
Radiation Tolerance	10 KRad
TRL Level	9
Interface	I2C (via EPS)
Mass	Varies by size
Connector	PCB edge connector
Coating	Anti-reflective
Vacuum Compatible	Yes

TRL 9 · Flight-proven

Triple-deployable solar array for CubeSats with three wing panels, maximizing power generation for high-power CubeSat and small satellite missions.

3 13

Solar Cell Type	Triple Junction GaAs
Cell Efficiency	29.5% (BOL)
Panel Type	Triple-Deployable
Compatible CubeSat Size	6U to 16U
Operating Temperature	-40°C to +100°C
Radiation Tolerance	10 KRad
TRL Level	9
Interface	I2C (via EPS)
Deployment Mechanism	Spring-loaded passive deployment
Connector	Flexible PCB harness
Coating	Anti-reflective
Vacuum Compatible	Yes
Number of Deployable Wings	3

S-Band transmitter for CubeSats up to 10 Mbps in amateur (2.4-2.45 GHz) or commercial (2.2-2.3 GHz) bands. PC/104 form factor, under 5W, under 100g.

1 12

Temperature	-25 to +61 C
Power	<5 W
Voltage	6V-12V (5V alternative)
Mass	<100 g
TX SNR	20 dB
Frequency (HSTX-C)	2.2-2.3 GHz
Frequency (HSTX)	2.4-2.45 GHz
RF Power	24-30 dBm in 2 dB steps
Channel Spacing	500 kHz
Spurious Response	<-60 dBc
Design Life	2 years in LEO
Dimensions	96 x 90 x 17.41 mm

Nadir-facing S-Band patch antenna for 3U CubeSats, 7 dBi gain, 60 degree beamwidth. Compatible with PULSAR-STX/HSTX. Proven on UKube-1.

2 9

Frequency (SANTC)	2.2-2.3 GHz
Frequency (SANT)	2.4-2.45 GHz
Beamwidth	60 degrees
Gain	7 dBi
S11	<-15 dB
Connector	SMA female
Mass	<50 g
Temperature Range	-40 to +85 C
Design Life	>2 years in LEO

Compact S-Band transmitter for CubeSats up to 2 Mbps in amateur (2.4-2.45 GHz) or commercial (2.2-2.3 GHz) bands. Flight-proven on UKube-1.

1 11

Temperature	-25 to +51 C
Power	<5 W
Voltage	6V-12V (5V alternative)
Mass	<100 g
TX SNR	20 dB
Frequency (STXC)	2.2-2.3 GHz
Frequency (STX)	2.4-2.45 GHz
RF Power	24-30 dBm in 2 dB steps
Channel Spacing	500 kHz
Spurious Response	<-60 dBc
Design Life	2 years in LEO

UHF/UHF nanosatellite transceiver in PC/104 form factor. 9600 bps GMSK, 1200 bps AFSK, AX.25, adjustable TX 27-33 dBm. Commercial (400-420 MHz) or amateur (430-440 MHz).

1 12

Operating Temperature	-25 to +61 C
Mass	<100 g
Voltage	3.3V, 5V
Frequency (UTRXC)	400-420 MHz
Frequency (UTRX)	430-440 MHz
Transmit DC Power	3-5.1 W
RF Power	27-33 dBm in 3 dB steps
Receive DC Power	<240 mW
Sensitivity	-115 dBm for 12 dB SINAD
Modulation	GMSK 9600 baud, AFSK 1200 baud
Protocol	AX.25, transparent mode
Dimensions	96 x 90 x 16.51 mm

VHF/UHF full-duplex transceiver for nanosatellites. VHF uplink 140-150 MHz, UHF downlink 400-440 MHz. 9600 bps GMSK, AX.25 protocol, PC/104 form factor.

2 13

Operating Temperature	-25 to +61 C
Mass	<100 g
Voltage	3.3V, 5V
VHF Frequency	140-150 MHz
UHF Frequency (VUTRXC)	400-420 MHz
UHF Frequency (VUTRXA)	430-440 MHz
Transmit DC Power	3-5.5 W
RF Power	27-33 dBm in 3 dB steps
Receive DC Power	162 mW
Sensitivity	-117 dBm for 12 dB SINAD
Modulation	GMSK 9600 baud, AFSK 1200 baud
Protocol	AX.25, transparent mode
Dimensions	96 x 90 x 16.51 mm

Low-profile X-Band patch antenna for CubeSat high-rate downlink 8.025-8.45 GHz. Standard 7.75 dBi or PLUS array 11.5 dBi. LHCP or RHCP.

1 15

Frequency Range	8.025-8.45 GHz
Bandwidth (XANT)	200 MHz
Bandwidth (XANT-PLUS)	425 MHz
Gain (XANT)	7.75 dBi +/-0.5 dB
Gain (XANT-PLUS)	11.5 dBi +/-0.5 dB
Axial Ratio (XANT)	<3 dB
Axial Ratio (XANT-PLUS)	<2 dB
Max RF Power (XANT)	2W
Max RF Power (XANT-PLUS)	5W
Mass (XANT)	<9 g
Mass (XANT-PLUS)	<29 g
Dimensions (XANT)	36 x 36 x 4.7 mm
Dimensions (XANT-PLUS)	58 x 58 x 4.7 mm
Temperature Range	-40 to +85 C
Design Life	2 years in LEO

TRL 9 · Flight-proven

High-performance on-board computer (OBC) for small satellites, featuring a Xilinx Zynq-7000 SoC for combined FPGA and ARM processing in a radiation-tolerant package.

1 20

Processor	Xilinx Zynq-7000 (dual ARM Cortex-A9 + FPGA)
CPU Speed	Up to 866 MHz
RAM	1 GB DDR3
Flash Storage	4 GB NAND
Operating System	Linux / FreeRTOS
Interfaces	SpaceWire (x4), UART (x6), I2C (x4), SPI, GPIO
Data Rate (SpaceWire)	Up to 200 Mbps
Power Consumption	~5 W (typical)
Supply Voltage	3.3 V / 5 V
Operating Temperature	-40°C to +85°C
Mass	~200 g
Dimensions	~100 x 100 x 25 mm
Radiation Tolerance (TiD)	20 kRAD
EDAC	Yes (memory error detection and correction)
Watchdog	Hardware watchdog timer
TRL Level	9
Boot Options	NOR Flash, SD Card, SpaceWire
Encryption	AES-256 support
Flight Heritage	>15 missions
Software Support	BSP, drivers, example code

Next-gen S-band TMTC SDR transceiver for SmallSats: TX up to 5 Msps QPSK in 2.200-2.290 GHz, RX BPSK 64 kSps-2 MSps in 2.025-2.110 GHz. End-to-end TMTC with QUASAR-WSANT.

2 16

Temperature	-25 to +60 C
Mass	270 g
Control and Data Interfaces	CAN, SPI, I2C
Power Consumption	3.5 W receive mode
TX Frequency	2.200-2.290 GHz
RF Output Power	-10 to 33 dBm in 0.25 dB steps
TX Modulation	Filtered OQPSK or QPSK CCSDS
TX Symbol Rate	Up to 5 MSps
TX Channel Coding	Convolutional/Reed-Solomon/Concatenated
RX Frequency	2.025-2.110 GHz
RX Symbol Rate	64 kSps to 2 MSps
RX Noise Figure	<2 dB
RX Modulation	Filtered BPSK CCSDS
RX Channel Coding	BCH
Dimensions	96 x 90 x 23 mm
Design Life	3-5 years

Wideband dual-polarization S-band antenna 2025-2290 MHz in single 83x83 mm compact unit. Pairs with QUASAR-STRX for complete TMTC solution. 5-6 year design life.

2 12

Frequency Band	2025-2290 MHz
Gain	>5 dBic
Axial Ratio	<3 dB
Half-power Beamwidth	60 degrees
Return Loss	>13 dB
Port Isolation	>10 dB (2110-2290 MHz)
RF Power	Up to 5 W at any port
Polarizations	RHCP / LHCP (two ports)
Mass	68.5 g
Dimensions	83 x 83 x 5 mm
Temperature Range	-20 to +60 C
Design Life	5-6 years

Miniature reaction wheel for CubeSats providing precision momentum exchange for fine attitude control on 1U-3U platforms.

2 10

Max Speed	±6000 RPM
Angular Momentum Storage	2.2 mNms
Max Torque	0.2 mNm
Motor Type	Brushless DC
Interface	I2C / CAN
Supply Voltage	5 V
Power Consumption (max)	~1 W
Operating Temperature	-40°C to +85°C
Mass	~100 g
Dimensions	~50 x 50 x 30 mm

TRL 8 · Qualified

Medium-class reaction wheel for 3U-16U CubeSats and small satellites, offering higher momentum storage for precision attitude control on larger platforms.

1 15

Max Speed	±6000 RPM
Angular Momentum Storage	4.0 mNms
Max Torque	0.4 mNm
Motor Type	Brushless DC
Interface	I2C / CAN
Supply Voltage	5 V / 12 V
Power Consumption (max)	~2 W
Operating Temperature	-40°C to +85°C
Mass	~200 g
Dimensions	~70 x 70 x 40 mm
Radiation Tolerance	10 KRad
TRL Level	8
Bearing Type	Angular contact ball bearings
Lubrication	Dry/vacuum-compatible
Vibration Qualification	ECSS-E-10-03

Desktop development kit for SmallSat SIRIUS-OBC-LEON3FT enabling flight software development and flat-sat testing. Powered by 12V mains adaptor.

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Processor	32-bit LEON3FT SPARC v8 @ 50 MHz
SDRAM	64 MB post-EDAC
Power Supply	9-15V (12V wall plug included)
SpaceWire	50 Mbps, RMAP, 2 interfaces
Serial Ports RS422/RS485	6 UARTs
GPIO	16 (3.3V logic)
Analog Input	24-bit, 31250 SPS, 8 channels
Dimensions	230 x 155 x 37 mm

Quad-core LEON4FT OBC at 250 MHz with TMR fault tolerance, 4 Gbit SDRAM, 4x SpaceWire. Linux 4.9 or RTEMS 5. Designed for 5-7 year LEO and deep space missions.

1 12

Design Life	5-7 years in LEO
Processor	Quad core LEON4FT SPARC v8 @ 250 MHz/core
Operating System	Linux 4.9 or RTEMS 5
SDRAM	4 Gbit + 2 Gbit EDAC
Operating Temperature	-30 to +60 C
Radiation (TiD)	20 kRAD (qualified >30 kRAD, Si)
SpaceWire	4x up to 300 Mbit, inbuilt router
CAN	2x CAN 2.0b
Input Voltage	5-12 V
Power Consumption	4 W nominal
Dimensions	100 x 100 x 15 mm
Mass	approx. 100 g

Desktop development kit for Sirius TCM LEON3FT with 32 GB mass storage and S/X-band CCSDS interfaces. Powered by 12V mains adaptor.

2 9

Processor	32-bit LEON3FT SPARC v8 @ 50 MHz
SDRAM	64 MB post-EDAC
Mass Memory Storage	32 GB post-EDAC
Power Supply	9-15V (12V plug included)
SpaceWire	50 Mbps, RMAP, 2 interfaces
CCSDS S-Band Interface	RS422 level
CCSDS X-Band Interface	LVDS level
Pulse Command Output	RS422 CPDU, 12 channels
Dimensions	230 x 155 x 37 mm

SmallSat mass memory and CCSDS stack module with LEON3FT at 50 MHz, 32 GB storage, S/X-band interfaces. TRL 9, flown since 2021, 5-year LEO design life.

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Expected Life	5 years in LEO
Processor	32-bit LEON3FT SPARC v8 @ 50 MHz
SDRAM	64 MB post-EDAC
Mass Memory Storage	32 GB post-EDAC
Operating Temperature	-30 to +60 C
Power Supply Input	4.5V to 16V
Nominal Power Consumption	1.3 W
SpaceWire	50 Mbps, 2 interfaces
CCSDS S-Band Interface	RS422 level
CCSDS X-Band Interface	LVDS level
Mass	130 g
Dimensions	95.89 x 90.17 x 17.20 mm

TRL 9 · Flight-proven

AAC Clyde Space's power conditioning and distribution unit delivering up to 2.5 kW for small satellites, with proven flight heritage and a modular, scalable architecture for diverse mission requirements.

3 20

Design Life	5-7 years in LEO
System Power	2.5 kW
Primary Bus Voltage	22-34 V
Solar Power Regulation	MPPT or S3R
Battery Charge Regulation	CC-CV
Idle Power Consumption Range	10 W Typically
Operating Temperature	-30°C to +60°C
Radiation Tolerance (TiD)	20 kRAD (qualified >30 kRAD Si)
Mass (5 Module Configuration)	3.9 kg
Mass (15 Module Configuration)	11.8 kg
Width (5 Module Configuration)	142 mm
Width (15 Module Configuration)	361 mm
Height	147 mm
Depth	249 mm
500 W Solar Array Configuration	20 x 28V LCLs - 6 x 5V LCLs - 6 x 12V LCLs
2.5 kW Solar Array Configuration	100 x 28V LCLs - 1.2 kW 50V output for electric propulsion
TRL Level	9
EM Lead Time	6 months
FM Lead Time	10 months
Flight Status	Flown 2024

TRL 9 · Flight-proven

An advanced SmallSat PCDU with an integrated Mission Control Computer, combining power management and satellite OBC functions into a single unit for streamlined satellite architecture.

3 21

Design Life	5-7 years in LEO
System Power	2.5 kW
Primary Bus Voltage	22-34 V
Solar Power Regulation	MPPT or S3R
Battery Charge Regulation	CC-CV
Idle Power Consumption Range	10 W Typically
Operating Temperature	-30°C to +60°C
Radiation Tolerance (TiD)	20 kRAD (qualified >30 kRAD Si)
Mass (5 Module Configuration)	3.9 kg
Mass (15 Module Configuration)	11.8 kg
Width (5 Module Configuration)	142 mm
Width (15 Module Configuration)	361 mm
Height	147 mm
Depth	249 mm
500 W Solar Array Configuration	20 x 28V LCLs - 6 x 5V LCLs - 6 x 12V LCLs
2.5 kW Solar Array Configuration	100 x 28V LCLs - 1.2 kW 50V output for electric propulsion
TRL Level	9
EM Lead Time	6 months
FM Lead Time	10 months
Flight Status	Flown 2024
MCC Integration	Mission Control Computer integrated

Flight-proven SmallSat OBC with 32-bit LEON3FT at 50 MHz, SpaceWire, EDAC-protected memory. TRL 9, flown since 2021, 5-year LEO design life. ITAR free.

1 14

Expected Lifespan	5 years in LEO
Processor	32-bit LEON3FT SPARC v8 @ 50 MHz
SDRAM	64 MB post-EDAC
NVRAM	16 kB post-EDAC
Nand Flash	2 GB post-EDAC
Operating Temperature	-30 to +60 C
Power Supply Input	4.5V to 16V
Radiation (TiD)	20 kRAD (qualified >30 kRAD, Si)
SpaceWire	50 Mbps, 2 interfaces
Serial Ports RS422/RS485	6 UARTs
GPIO	16 (3.3V logic)
Nominal Power	1.3 W
Mass	130 g
Dimensions	95.89 x 90.17 x 17.20 mm

TRL 9 · Flight-proven

Miniature sun sensor for CubeSats providing coarse solar vector determination for attitude estimation and safe mode operations.

1 12

Field of View	±60° (half-angle per axis)
Accuracy	<1° (1σ) in FOV
Update Rate	Up to 100 Hz
Interface	I2C / Analog
Supply Voltage	3.3 V
Power Consumption	<15 mW
Operating Temperature	-40°C to +100°C
Mass	~5 g
Dimensions	~20 x 20 x 6 mm
Radiation Tolerance	10 KRad
TRL Level	9
Albedo Rejection	Yes (software filter)

TRL 9 · Flight-proven

Compact star tracker for CubeSats and small satellites providing high-accuracy 3-axis attitude determination using star pattern recognition.

2 15

Attitude Accuracy (cross-boresight)	<10 arcsec (1σ)
Attitude Accuracy (roll)	<30 arcsec (1σ)
Update Rate	Up to 5 Hz
Acquisition Time	<5 s (initial), <1 s (tracking)
Field of View	15° x 15°
Limiting Magnitude	Mv = 6.5
Interface	RS-232 / SpaceWire
Supply Voltage	5 V / 12 V
Power Consumption	~3 W
Operating Temperature	-30°C to +60°C
Mass	~300 g
Dimensions	~100 x 100 x 80 mm
Radiation Tolerance	10 KRad
TRL Level	9
Star Catalog	Embedded (>100,000 stars)

TRL 8 · Qualified

High-performance star tracker for small satellites providing sub-arcsecond attitude accuracy for demanding pointing and science missions.

2 17

Attitude Accuracy (cross-boresight)	<3 arcsec (1σ)
Attitude Accuracy (roll)	<10 arcsec (1σ)
Update Rate	Up to 10 Hz
Acquisition Time	<2 s (initial), <0.2 s (tracking)
Field of View	10° x 10°
Limiting Magnitude	Mv = 7.5
Interface	RS-422 / SpaceWire
Supply Voltage	5 V / 12 V
Power Consumption	~5 W
Operating Temperature	-30°C to +60°C
Mass	~500 g
Dimensions	~120 x 120 x 100 mm
Radiation Tolerance	20 KRad
TRL Level	8
Star Catalog	Embedded (>200,000 stars)
Stray Light Rejection	Sun exclusion >30°, Moon >15°
Detector	Large format CMOS APS

High-performance reaction wheel for small satellites: 1.2 Nms momentum storage, 47.1 mNm max torque, 1.5 kg. Tested to NASA GEVS, flown since 2019.

1 7

Maximum Torque	47.1 mNm
Maximum Rotation Rate	6500 rpm
Total Momentum Storage	+/-1.2 Nms
Mass	1.5 kg
Peak Power	24 W
Dimensions	135 x 135 x 82 mm
Operating Temperature	-40 to +85 C

TRL 9 · Flight-proven

UHF/VHF full-duplex transceiver for CubeSats supporting half-duplex and full-duplex operation with software-defined radio architecture.

2 23

TX Frequency Range	400-450 MHz (UHF)
RX Frequency Range	130-175 MHz (VHF)
TX Output Power	Up to 2 W
RX Sensitivity	<-118 dBm
Data Rate	1.2 to 38.4 kbps (uplink/downlink)
Modulation	GMSK, FSK, BPSK (configurable)
Duplex Mode	Half-duplex / Full-duplex
Interface	RS-232 / I2C
Supply Voltage	5 V / 3.3 V
Power Consumption (TX)	~4 W
Power Consumption (RX)	~0.5 W
Operating Temperature	-40°C to +85°C
Mass	~110 g
Dimensions	~90 x 90 x 15 mm
Radiation Tolerance	10 KRad
TRL Level	9
Protocol Support	AX.25, custom framing
Frequency Tuning Step	1 kHz
Frequency Stability	<±2 ppm
Channel Filters	Programmable
AGC	Yes
RSSI Output	Yes
Error Correction	FEC (optional)

TRL 9 · Flight-proven

Modular aluminum CubeSat structure for 1U to 16U form factors, offering design flexibility, high stiffness-to-mass ratio, and compatibility with standard CubeSat deployers.

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Material	Aluminum 6061-T6
Available Sizes	1U, 2U, 3U, 6U, 12U, 16U
Surface Finish	Anodized or chromate conversion coating
Rail Compliance	CubeSat Design Specification (CDS)
Deployer Compatibility	ISIS, Nanoracks, and standard deployers
Mass (1U)	90 g
Mass (3U)	180 g
Mounting Interface	PC/104 compatible
Operating Temperature	-40°C to +85°C
Radiation Tolerance	N/A (passive structure)
TRL Level	9
Lead Time	8-12 weeks
Custom Configurations	Available on request

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AAC Clyde Space

About AAC Clyde Space

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