Educational
CubeSat

On 9 August, the first ever private spacecraft Geoscan-Edelveis, designed in Saint Peterburg, was sent into space from the Baikonur Cosmodrome. For the first time in Russia, a CubeSat 3U is provided with a silicon wafer, with 22 772 names from all over the world having been applied onto it by the method of ion-beam lithography. The map shows where our spacecraft ‘passengers’ come from.

Presenting
Geoscan 1U
and Geoscan 3U

The CubeSats are designed for the conduct of school and university experiments in near-Earth space

CubeSat payloads

Small scientific instruments

Monitoring electron, proton and nucleus flows, ultraviolet, and gamma rays in the Earth’s upper atmosphere.
Carrying out biological experiments.

Remote sensing cameras

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 tasks for the CubeSats

The CubeSats Geoscan 1U and Geoscan 3U are 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.

Learn more

Assembled weight (without a payload)	0.8-1 kg
Maximum weight including а payload	1.33 kg
Dimensions folded	110х110х113.5 mm
Maximum weight of a payload	0.33…0.50 kg
Available volume for a payload	82x82x60 mm
Available supply for a payload	12 V / 2 A 5 V / 3 A
Payload average power at LEO	500 mV
Available maximum output of a payload	Up to 35 W
Storage battery capacity	40 W*h
Battery type	Li-ion 2S 7200 mAh
Battery nominal voltage	7.4 V
Number of solar panels	5 pcs
Peak output produced on 1 solar panel in LEO	1.5 W
Onboard interface	I²C, UART
Payload interface	UART / CAN / RS-485
Antenna type	UHF dual dipole X-band patch antenna
Control radio channel frequency	435-438 MHz, frequency modulation
Data transmission speed through radio channel	1200, 2400, 4800, 9600, 14400, 19200 bit/s
High-speed transmitter frequency	10.4 GHz, frequency modulation
High-speed radio channel data rate	Up to 1 Mbit/s
Stabilization system	Electromagnetic
Orientation determination	2 three-axis magnetometers, 6 solar sensors
Orientation modes	Stabilization of rotation, pointing to the Sun or to the Earth coordinates according to a program
Accuracy of orientation system	5º
Design lifetime	At least 2 years

№	Specification	Modification 1	Modification 2
1	Assembled weight (without a payload)	under 1.9 kg	under 2.4 kg
2	Maximum weight including а payload	6 kg
3	Dimensions folded (with separation system locked)	110х110х340.5 mm
4	Maximum weight of a payload	4.1 kg	3.6 kg
5	Available volume for a payload	90×90×170 mm
6	Available supply for a payload	stabilized 5 V / 2 А stabilized 3.3 V / 2 А unstabilized 7…8.4 V / 2А
7	Payload average power at LEO (specified for a specific orbit)	3 W
8	Available maximum output of a payload (specified for a specific orbit)	up to 15 W for one payload (expansion up to 60 W is available)
9	Storage battery capacity	40 W*h
10	Battery type	Li-ion 2S 7200 mAh
11	Battery nominal voltage	7.4 V
12	Number of solar panels	up to 13 pcs.
13	Peak output produced on 1 solar panel in LEO	5.5 W
14	Onboard interface	CAN
15	Payload interface	CAN / UART / SPI
16	Control radio channel frequency	435-438 MHz, frequency modulation
17	Data transmission speed through radio channel	9600, 19200 bit/s
18	High-speed transmitter frequency	-	10.4 GHz, phase modulation
19	High-speed radio channel data rate	-	up to 10 Mbit/s
20	Antenna type	dual UHF dipole	dual UHF dipole; X-band – antenna array
21	Stabilization system	magnetic coils	magnetic coils, flywheels
22	Orientation modes	B-dot algorithm, pointing to the Sun or to the Earth coordinates according to a program
23	Accuracy of orientation system	up to 3º
24	Design lifetime	over 2 years

EducationalCubeSat

Educational
CubeSat