Products

The highest performance platform of Solar Space, easily adaptable to handle complex
Earth Observation, IoT, science, and exploration missions

Bus Mass - 6-8 kg (configuration dependent)
Available Payload Mass - 14-16 kg (configuration dependent)
Available Payload Volume - 197 x 197 x 225 mm3
Average Payload Power Available - 20-45 W (configuration dependent)
Available Power Buses - 3.3 V, 5 V, customizable 6-12 V and Battery raw
Telemetry Data Rate up to - 2 Mbps
Payload Data Rate up to - 1 Gbps

Wide frequency range in S-band

Feautures :

Frequency Ranges - 2025-2110 MHz and 2200-2290 MHz
Half Power Beam Width (HPBW) - 70 deg
Gain - 5+ dBi
Polarization - Right Hand Circular
Mass - 115 g
Custom Mounting - X/Y or Z CubeSat mounting
RF Output Power up to - 4 W

Dimensions 90mm×90mm×30mm（±1mm）
Mass 420±30g

More info available on request

We offer more than 20 types of magnetorquer rods for various satellite missions.
A Magnetorquer is a satellite attitude control system that interacts with the geomagnetic field to create magnetron momentum and is often used in conjunction with a reaction wheel

Dimensions 90mm×90mm×40mm（±1mm）
Mass 540±30g

More info available on request

We offer more than 20 types of magnetorquer rods for various satellite missions.
A Magnetorquer is a satellite attitude control system that interacts with the geomagnetic field to create magnetron momentum and is often used in conjunction with a reaction wheel

Deployable 2U UHF antenna fully compliant with the 6U CubeSat standard

Feautures :
Amateur Frequency Range - 435-438 MHz
Commercial Frequency Range - 400-403 MHz
Type - Omnidirectional
Gain - > 0 dBi
Polarization - Circular
Mass - 201 ± 20 g
Monitoring And Control Interfaces - RS-485, I2C, UART

Small Satellite Reaction Wheels
Physical
Mass - 60g
Dimensions - 28x28x26.2mm
Operating temperature - -10°C to 60°C
Vibration - 14g RMS
Radiation - 24kRadElectrical
Supply voltage - 3V3 & 6.4-16V
Average power (2000 rpm) - 150mW
Peak power - 0.65W
Communications - I2C/UART/CANPerformance
Speed range - ±8000
Momentum @ max speed - 1.77mNms
Max torque - 0.23mNm
Static imbalance - <0.003 g·cm
Dynamic imbalance - <0.005 g·cm

Small Satellite Reaction Wheels
Physical
Mass - 90g
Dimensions - 33.4x33.4x31.5mm
Operating temperature - -10°C to 60°C
Vibration - 8.9g RMS
Radiation - 24kRadElectrical
Supply voltage - 3V3 & 6.4-16V
Average power (2000 rpm) - 190mW
Peak power - 2.3W
Communications - I2C/UART/CANPerformance
Speed range - ±6000
Momentum @ max speed - 3.6mNms
Max torque - 2.3mNm
Static imbalance - <0.004 g·cm
Dynamic imbalance - <0.014 g·cm

Flight-proven Electric Power System (EPS)

Feautures :
Input Channels - 3 (one for each CubeSat axis)
Input Voltage (Per Solar Panel Channel) - up to 5.5 V
Input Current (Per Solar Panel Channel) - up to 1.8 A
Six Connectors For - the solar panels
Integrated Blocking Diode For Each - solar panel connector
Battery Pack Power - 10.2 Wh (20.4 Wh with EPS I Plus)
Battery Pack Voltage - 3.7 V nominal
Mass - 208 g
Stackable Battery Packs - up to 8 A
Output Power Buses - 3.3 V, 5 V, BCR (5 V max) and Battery raw
Interfaces - UART, I2C, USB-C
Switches - Two deployment and one Remove Before Flight (RBF)
Control - Six general purpose outputs for shutdown/reset of external modules
Interfaces - UART, I2C, USB

Flight-proven Electric Power System (EPS)

Feautures :
Input Channels - 3 (one for each CubeSat axis)
Input Voltage (Per Solar Panel Channel) - up to 5.5 V
Input Current (Per Solar Panel Channel) - up to 1.8 A
Integrated Blocking Diode - for each solar panel connector
Battery Pack Power - 20.4 Wh (10.2 Wh with EPS I)
Battery Pack Voltage - 3.7 V nominal
Mass - 298 g
Stackable Battery Packs - up to 8 A
Output Power Buses - 3.3 V, 5 V, BCR (5 V max) and Battery raw
Interfaces - UART, I2C, USB-C
Switches - Two deployment and one Remove Before Flight (RBF)
Control - Six general purpose outputs for shutdown/reset of external modules
Interfaces - UART, I2C, USB

The next generation of NanoSat and MicroSat Electric Power System (EPS)

Feautures :
Input Channels - 3 per battery pack
Redundancy - Fully redundant Solar Panel connectors
Input Voltage (Per Solar Panel Channel) - 10 to 36 V
Input Current (Per Solar Panel Channel) - up to 4 A
Stackable Battery Packs - up to 4 packs for a maximum power of 1 kW
Current Limitation - Configurable both for input and output channels
Integrated Blocking Diode - for each solar panel connector
Charge/Discharge Mode Voltage And Heater Thresholds - configurable
Standard Battery Pack Capacity - 80.4 Wh
Standard Battery Pack Voltage - 35.1 V
Mass (EPS + Battery Pack) - 1280 g
Output Power Buses - 2x3.3 V, 2x5 V, 1xProgrammable (6-12 V) and Battery raw
Switches - Deployment and Remove Before Flight (RBF)
Interfaces - RS-485, USB

Versatile On-board Computer for Cube, Nano and Microsat missions

Feautures :
High-performance AVR32 MCU with advanced power saving features
512 KB build-in flash
128 MB NOR flash (On two dies of 64 MB each)
32 kB FRAM for persistent configuration storage
32 MB SDRAM
RTC clock
On-board temperature sensors
Interfaces:
I2C, UART, CAN-Bus
8 external ADC channels that can also be used as GPIO
External SPI with 3 chip selects
Cubesat Space Protocol (CSP)
GOSH interface for check-out
Attitude control system features:
3-Axis magneto resistive sensor
3-Axis gyroscope
3 bidirectional PWM outputs with current measurements
I2C interface for GomSpace Sensor Bus (GSSB)
Electrical features:
2 x 20-position hard-gold plated FSI one-piece connector

Small and powerful battery module for CubeSats

Feautures :
18650 Li-Ion cells with a nominal capacity of 2600 mAh
Two configurations are available:
2P-2S: 6 - 8.4 V & 5.2 Ah
1P-4S: 12 - 16.8 V & 2.6 Ah
Integrated temperature sensors with digital interface
Battery heater
Auxiliary MOSFET switch (e.g. to drive thermal knives for deployables)
Stackable for increased capacity
Fits standard PC104
ISS launch compliant version availabl