Geoscan engaged in the development of CubeSat small spacecraft in 2021, becoming one of the manufacturers of platforms for educational satellites under the Space-π project of the Foundation for Assistance to Innovations.
CubeSats are standardized educational small satellites. The dimensions of the basic 1U satellite are 10×10×10 cm with a mass not exceeding 2 kg. CubeSats can be up to 24U (20×30×40 cm) in size, and their size depends on the dimensions of the onboard systems and payloads. They are used to teach satellite design, programming and assembly, amateur radio communication sessions, flight tests of onboard systems and instruments in the near-Earth orbit, and for school, student and scientific space experiments.
In 2022, the first private small satellite designed in Saint Petersburg, Geoscan-Edelveis, was launched from the Baikonur Cosmodrome. The first domestic gas engine for small spacecraft was successfully tested on the CubeSat, and in 2023, Geoscan's first client satellite, StratoSat TK-1, built for Stratonautica, was launched into space from the Vostochny Cosmodrome. It was used to deliver six TinySat picosatellites into the orbit.
Geoscan 3U
The Geoscan 3U satellite platform can carry up to four payloads up to 2U in volume: Earth remote sensing (ERS) cameras and small scientific instruments.
CAN bus is used for connection of the payload. Also, a high-speed configurable bus consisting of four wires with LVDS physical layers is used to transfer large amounts of data from the payload.
A separate interface board, on which other connection interfaces can be implemented in agreement with the platform developers, is developed for each satellite for connection with the payload.
Each unit is equipped with a 2 MP overview camera. Magnetic and flywheel systems are used for orientation in space.
CubeSat Geoscan 3U
- 1,8 kg assembled weight
- 6 kg max weight including payload
- 100х100х340,5 mm dimensions folded
Geoscan 3U specifications
| № | Specification | Modification 1 (truncated configuration) | Modification 2 (full set) |
| 1 | Assembled weight (without a payload), kg | 1,8 | 2,3 |
| 2 | Maximum weight of a payload, kg | 4.2 kg | 3.7 kg |
| 3 | Maximum weight including а payload, kg | 6 kg | |
| 4 | Dimensions folded (with separation system locked), mm | 100х100х340,5 (100x100x376,5 with Tuna Can) |
|
| 5 | Available volume for a payload, mm | 95х95х180 (~2U) | |
| 6 | Radiation protection | aluminum sheet 1.2 mm | |
| 7 | Available supply for a payload | stabilized 3,3…12 В / 2 А, unstabilized 7…8,4 В / 2А |
|
| 8 | Payload average power at LEO (specified for a specific orbit), W | 2 | |
| 9 | Available maximum output of a payload (specified for a specific orbit), W | 15 | |
| 10 | Storage battery capacity, W*h | 50 | |
| 11 | Battery type | Li-ion 2S 7200 mAh | |
| 12 | Number of solar panels, pcs. | up to 12 (silicon) | |
| 13 | Peak output produced on 1 solar panel in LEO, W | at least 1 | |
| 14 | Onboard interface | CAN | |
| 15 | Payload interface | CAN / UART / SPI, others on request | |
| 16 | Low-speed radio channel frequency, MHz | 435-438 | |
| 17 | Data transmission speed through low-speed radio channel, bit/s | 2400, 9600, 57600 | |
| 18 | High-speed transmitter frequency, GHz | - | 10,45-10,5 |
| 19 | High-speed radio channel data rate, Mbit/s | - | up to 250 |
| 20 | Radio command channel signal modulation type | frequency | |
| 21 | Type of modulation of a high-speed radio channel signal | - | phase |
| 22 | Antenna type of low-speed radio channel | turnstile | |
| 23 | Antenna type of high-speed radio channel | - | antenna array |
| 24 | Maximum transmitter power, dBm | 30…32 | |
| 25 | Orientation system | magnetometers, solar sensors, horizon sensor, inertial module |
magnetometers, solar sensors, horizon sensor, inertial module GNSS receiver |
| 26 | Attitude support system | magnetic coils | magnetic coils, flywheels |
| 27 | Stabilization modes | B-Dot | B-Dot triaxial orientation: - in the sun, - at nadir, - to a point on Earth |
| 28 | Orientation accuracy | up to 1˚ | |
| 29 | Attitude system accuracy | - | up to 1˚ |
| 30 | Additionally | 2 MP technology camera, Software update via low-speed radio channel, Management of small spacecraft for 1 year after launch |
|
| 31 | Documentation | Passport, Manual |
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CubeSat payloads
- remote sensing cameras;
- small scientific instruments.
Scientific instruments are used in order to monitor electron, proton and nucleus flows, ultraviolet, and gamma rays in the Earth’s upper atmosphere and also for carrying out biological experiments.
The tasks for the CubeSats
- training school and university students in the design, programming and assembly of real spacecrafts;
- following their test flights in LEO (low Earth orbit);
- organising competitions and experiments via the amateur radio frequency network.
The CubeSat Geoscan 3U is being developed within the parameters of the Russian educational project for the creation of satellite constellation (Space-π) for student career guidance which is supported by the Innovation Assistance Foundation.