6u satellite

Space Inventor’s 6U satellite is configured from our modular subsystems, which provides the opportunity for buyers to tailor the satellite exactly to their needs. Our highly iterative development process secures an easy and safe integration procedure and provides the opportunity for module interchangeability. This procedure, which is seen across all Space Inventor platforms, relies on thorough analysis as well as subsystems that are updated at least once a year. The 6U satellite is built with shielded hi-reliability subsystems where each system has its own radiation shielding, EMI Shielding, thermal conduction path, and mechanical support. The 6u satellite platform can be extended with deployable solar panels where the ADCS system can provide Nadir or ground tracking whilst optimizing the power generation by rotating the entire satellite across the bore-axis optimizing the solar energy harvesting.

All Space Inventor satellite platforms have a design lifetime of 5 years.

Applications of Space Inventor’s satellite platform:

  • Educational missions
  • BIU missions
  • In-orbit demonstration missions
  • Scientific missions
  • IoT missions
Payload mass
3-6 kg
Payload Volume
2-4 unit
Payload power
100 W
Data downlink
2x S/X band 4 - 200 Mbps
Flight Heritage

Subsystems in Space Inventor’s 6U satellite


The satellite platform is designed by using the high reliable subsystems made by Space Inventor providing high performance, low EMI and very easy integration. The basic avionics consists of four basic elements, the power plant for power generation, conditioning and distribution, on-board data handling, communication to ground segment and the attitude determination and control system.

The satellite platform is designed with reliability and performance as the primary design drivers. It uses the shielded hi-rel subsystems: Batteries, power conditioning and distribution, communication and attitude control. Each system has its own radiation shielding, EMI shielding, thermal conduction path, and mechanical support. The satellite is designed not only for extreme ruggedness but also ease of integration. Any side panel can easily be removed and are then free with no cables attached.

Power Plant


The complete Space Inventor power systems consisting of the MPPT-P3, BAT-P3, PCDU-P3 is providing an agile and effective solution. The power systems provide all functionalities needed from maximizing power input from the photovoltaic cells, storing power and providing regulated output channels to individual subsystems. On the output side an unregulated V-bat is also available.

  • Solar panels – deployable and/or body mounted
  • Maximum power point tracking (MPPT-P3)
  • Battery pack (BAT-P3)
  • Power conditioning and distribution unit (PCDU-P3)



The MPPT-P3 is a 7-channel maximum power point tracker and battery charger module, designed to condition the power delivery from satellite solar panels to the battery in order to achieve maximum efficiency. The system consists of six variable frequency DC-DC buck converters and a single variable frequency boost-converter, that ensure optimal operating voltage for each solar cell array at all temperatures and irradiance levels. After conversion, the channels are combined through ideal diodes to minimize loss, and connected to the battery output.

A configurable end-of-charge setting will stop charging at a certain voltage level in order to prolong battery life. When components reach end-of-life, a pass-through mechanism will route the solar output directly to the battery bus, whereby functionality is not entirely lost. Likewise, if the on-board MCU is disabled, each MPPT channel has a fixed voltage fallback. Housekeeping data for all channels are available through CSP telemetry. Appreciating that the solar panels are often combined with external sun and temperature sensors, each solar panel connector are equipped with a protected battery supply and CAN bus interface.

The MPPT-P3 is built for durable, simple and robust satellite integration

MPPT-P3 Features

  • Maximum power point tracker for satellite solar panels
  • Integrated battery change management
  • 7 solar cell string input channels w. Up to 2 x 12 cells per channel
  • Ruggedized enclosure for maximum thermal performance, radiation shielding and EMI reduction
  • Suitable for microsatellites and CubeSats
  • Measurements: (L, W, H) 91.14 x 94 x 11 mm // 150 g
BAT100-P3 features


  • Integrated battery module for satellites
  • 8 LiIon cells configurable for 14.4 or 28.8V at 92 Whr
  • Cell balancing and heater
  • input/output current limiting
  • Ruggedized enclosure for maximum thermal performance, radiation shielding and EMI reduction
  • Suitable for microsatellites and cubesats
  • Measurements: (L, W, H) 91.14 x 94 x 41.2 mm // 655 g



The PCDU-P3 is a twelve-channel power conditioning and distribution unit in a rugged, compact and modular enclosure. The system features six independent and customizable step-down converters and one boost converter, that can be connected to output channels as required. The PCDU-P3 architecture allows designers to allocate one subsystem per power channel, whereby many of the EMI issues experienced on shared power busses are eliminated. This makes the PCDU-P3 ideal for missions with demanding payloads and sensitive receivers.

To minimize thermal stresses and mitigate radiation, the PCDU-P3 is enclosed in 1.5 mm (min.) Al. The PCB is top-side only and mounted flush with the bottom of the enclosure, which reduces thermal resistance to the satellite body. With a standing height of only 12 mm and PC104 compatible mounting holes, the PCDU-P3 easily integrates with existing busses, without occupying excess stack space. All outputs have independent power monitoring and latch-up protection. Monitoring and configuration is enabled through the CSP protocol and onboard MCU. For convenience all connectors are CAN enabled.


PCDU-P3 features

  • Power conditioning and distribution unit for satellites
  • 12 power output channels with protection and monitoring
  • 6 buck converters and 1 boost converter with configurable voltages and routing
  • Power metering, latch-up protection, battery discharge management and protection, programmable on/off timers
  • Ruggedized enclosure for maximum thermal performance, radiation shielding and EMI reduction
  • Suitable for microsatellites and CubeSats
  • Measurements: (L, W, H) 91.14 x 94 x 13 mm // 138 g

Attitude Determination and control system


Space Inventor’s attitude and orbit determination and control solutions are comprised by our wide range of high-performance, rugged and modular AOCS avionics products. The range of modules spans from very small cubesat reaction wheels to large reaction wheels for satellites up to several hundred kilograms. Furthermore, we manufacture a best-in-class star tracker, integrated fine sun sensors, magnetorquers, GPS modules, ADCS computers and software which we use to configure tailored ADCS and AOCS solutions for both simple cubesats and highly advanced science satellites.The ADCS system can provide Nadir or Ground Target tracking mode and can be tailored to the specific orbit and mission.


  • Includes fully featured ADCS software
  • Pointing modes include: Nadir, sun tracking, ground spot tracking, inertial pointing, dual target (e.g. nadir while sun tracking)
  • Actuators: 4 reaction wheels, redundant three-axes magnetorquer rods
  • Sensors: 5 fine sun sensors, 5 gyroscopes, 5 magnetometers
  • Performance: 1 degree pointing accuracy (for arcsecond pointing requirements Space Inventor’s Star Tracker can be employed for improved attitude knowledge determination)
  • The software runs on the redundant OBC-P3

Momentum Wheels


Space Inventor’s 6U satellite uses a fully integrated reaction wheel unit for high performance satellite attitude control for  with mission lifetime of 5 years (minimum). The WHL-50 wheel is an integrated 3-phase outrunner Permanent magnet synchronous motor (PMSM) with 14 rare-earth magnet poles in the rotor and 12 teeth in the stator. Material for the body is Al-7075-T6, rotor is made of ferritic stainless steel while the magnets are Neodymium.

The rotor is axially suspended between two hybrid ceramic high precision bearings chosen for long life and low friction in vacuum conditions. The wheel is commutated by its own internal microcontroller, which runs the control loop to control speed and acceleration upon commands from the ADCS computer.

For higher performance attitude control it is recommendable to use Space Inventor’s WHL-200 with a momentum storage of 200 mNms and 25 mNm tourque.


WHL-50 features

  • Compact, integrated reaction wheel unit for 3-6 kg cubesats
  • Momentum storage: 50 mNms @ 12.000 RPM
  • Torque: 5 mNm. Nominal flat torque box of 2 mNm from -40 to +40 mNms
  • Control modes: Momentum, torque, speed or motor voltage
  • Automatic motor flux reduction (FOC)
  • 3-phase Permanent magnet synchronous motor (PMSM)
  • Can bus interface with CSP
  • Rotor inertia: 34.4 x 10-6 kg mm2
  • Measurements: 50 x 50 x 25 mm // 180 g



The highly integrated Fine Sun Sensor (FSS-1G2), integrated inSpace Inventor’s 6U satellite, uses four photodiodes to estimate the sun direction vector with a precision of 1 degree. The module has a built-in micro controller which enables connectivity to a CSP network via CAN bus and readily integrate with an attitude determination and control system such as e.g. ADCS-P3 and ADCS-R3. In addition to the sun sensor functionality, the module includes a 2-axis gyroscope and 3-axis magnetometer making it a versatile attitude sensing component. The 1G2 variant is an upgraded version of the previous 1G model which has flight heritage. 1G2 is expected to be launched in Q1 2022.


FSS-1-G2 Features

  • 2-axis sun direction sensor based on quad photo diode array
  • 1 degree precision
  • 55 degree half-cone FoV
  • Integrated 3-axis magnetometer
  • 0.25mG per LSB resolution
  • 0.4mG total RMS noise
  • Magnetic field direction accuracy 1º
  • Integrated 2-axis Gyro
  • Ultralow noise: 0.004°/s/√Hz
  • 5-28V unregulated power input
  • Data interface: CAN bus with CSP2.0
  • Measurements (L, W, H): 40x20x10 mm



The communication system consists of a VHF/UHF TT&C radio for telemetry and commanding the spacecraft. The radio system can be configured to different operating frequencies according to the frequency license obtained from ITU for space operation. A high data-rate radio in S-band (STTC-P3) can also be included in the configuration with a patch antenna mounted on face pointing Nadir.


  • UHF/VHF radio (TTC-P3)
  • UHF/VHF antenna (DMA)
  • S and X-band transmitter (STTC-P3)



The TTC-P3 is a hot-redundant satellite telemetry, tracking and command (TT&C) radio with two half-duplex VHF/UHF transceiver designed to enable robust and reliable satellite communication. The TTC-P3 is intended to be used in an antenna diversity scheme, where each channel is connected to orthogonal and cross-polarized antennas. Hereby a good omnidirectional gain pattern can be achieved, which makes signal reception nearly independent of satellite attitude. Careful receiver design provides a noise figure below 2 dB, which, combined with concatenated convolutional and Reed-Solomon decoding, ensure excellent sensitivity. Realizing that interference have proved problematic over certain regions, the TTC-P3 also features a 60 dB out-of-band rejection filter.


TTC-P3 features

  • 2 Half-Duplex VHF/UHF Transceivers
  • Data-rate: 4800 – 38400 kbps nominal (up to 115.200 available upon request)
  • Frequency bands: 130-140,140-150, 400-410 and/or 430-440 MHz
  • 30 dBm output power at > 50% PA efficiency
  • Noise Figure: <2 dB
  • Modulation: GMSK
  • FEC: Convolutional Coding (K=7, r=½) and Reed Solomon (RS-223,255)
  • Measurements: (L, W, H) 91.14 x 94 x 11 mm // 143 g



The STTCX-P3 is a software defined satellite transceiver offering a versatile S/X-band transceiver module for high-speed communication and ranging solution for both LEO and GEO missions. The transceiver is designed to work with the latest CCSDS Cat A recommendations for high data rate transmissions and high spectral efficiency. Using constant envelope GMSK or low crest factor SRRC filtered OQPSK modulation for higher power amplifier efficiency and lower linearity requirements.

The ranging functionality supported is transparent pseudo noise ranging according to CCSDS 414.0-G2 standard where the transceiver frequency-translates the uplink ranging signal to the downlink without code acquisition (i.e., non-regenerative ranging or turnaround ranging) – Eventually active regenerative ranging system will be supported The SDR is based on a powerful Xilinx Zync-7030 SoC and high-performance Analog Devices SDR front-end, the AD9361.



STTCX-P3 features

  • Channels: 2 receive, 2 transmit
  • 2 x S-band uplink : 2025 – 2110 MHz
  • 1 x S-band downlink: 2200 – 2290 MHz
  • 1 x X-band downlink: 8025 – 8400 MHz
  • Tx power up to 2 Watt
  • Rx noise figure: 5 dB (TBD)
  • Full duplex
  • Tx amplifier bypass function
  • CCSDS compliant (401.0-B-30)
  • GMSK or OQPSK – 9600 bps to 20 Mbps
  • FEC: Convolutional Coding (K=7, r=1⁄2) and Reed Solomon (RS-223,255)

Onboard data


Space Inventor provides various onboard computing platforms suitable for hot/cold redundancy solutions used for Space Inventor’s subsystems and management of valuable payloads.


  • OBC-P3 (Redundant Cortex-M7)
  • Z7000 (Redundant Zync-7030)



The OBC-P3 is an onboard computing platform consisting of two independent ARM Cortex-M7 modules, each with separate power supply, interfacing, and storage. The dual architecture makes the OBC-P3 a suitable choice for hot/cold redundancy solutions often desired for mission critical subsystems, such as T&C, GNC, or management of valuable payloads. Each on-board computer has a large memory storage of 64GB for user data.

The application of the OBC-P3 is further enhanced by the powerful DSP functionality provided with the Cortex-M7 architecture, which makes it possible to port heavy floating-point processing such as ADCS or RvD algorithms without severe performance penalties and error-prone quantization. By default, the OBC-P3 is configured either as an on-board data handling unit with telemetry collection functionality, or as an OS-only installation for designers to write their own application


OBC-P3 features

  • Two fully independent onboard computer modules in shared enclosure
  • 2x ARM® Cortex-M7 Main Processing Units
  • Memory x 2: 384 kB SRAM, 64 GB eMMC, 32 kB FRAM, 2 MB on-chip flash
  • Ruggedized enclosure for maximum thermal performance, radiation shielding and EMI reduction
  • Suitable for microsatellites and CubeSats
  • Measurements: (L, W, H) 91.14 x 94 x 13 mm // 120 g



The Z7000-P3 is a powerful system on a chip FPGA based payload computer with a dual-core ARM Cortex-A9 MPCoreTM and FPGA logic with 125K programmable cells. The Z7000-P3 is a suitable choice as a payload computer with requirements for high data-rates and processing capabilities. The Z7000-P3 offers a broad range of interfaces including LVDS/SpaceWire and up to 1Gb Ethernet. Furthermore traditional OBC interfaces such as CAN, UART, I2C etc are supported. For standard control interface for commanding and telemetry, Space Inventor recommends using the CAN bus. For storage of payload generated data a mass memory system is included with a capacity up to 64GB.


z7000-p3 features

  • On-board computer based on Xilinx Zync 7030 SoC
  • Dual ARM® Cortex-A9 Main Processing Units 667 MHz
  • Memory: 256KB on-chip memory, 512 MB ECC or 1GB RAM, up to 64GB mass storage
  • FPGA: 125K Programmable Logic Cells
  • Interfaces: 2 x CAN, 1 x Ethernet, 1 x SPI, 1x RS232 UART, 16 x LVDS, 1 x RS422 UART, 4 x ADC, 1 x I2C
  • Power consumption: <1.5 W idle. Up to 20 W
  • Measurements: (L, W, H) 91.14 x 94 x 13 mm // 155 g