a micro-satellite platform with common equipment.
This platform was designed for about 100 kg mass satellites. Its position control uses a star sensor, some gyrometers and reaction wheels. The orbit control will be done by an hydrazine system.
The on-board management centralised, build using a 10 MIPS micro processor T805. A mass memory is available for the data storage. The telemetries and the telecommande use CCSDS standard.

a payload which is formed by:

a technological component which includes:

a 8 Gb mass memory
a high rate telemetry
theAOC-GPS experiment (Autonomous Orbit Control by GPS)
a photonic setting off for a pyrotechnical system (PYROLASER)
the thermic control coating qualifying (THERME)

a scientific component which includes the following sensors:

IMSC: a triaxial set of 3 magnetic sensors (Search Coil),
ICE: a 4 electrical sensor system,
IAP: a plasma analyser,
ISL: a Langmuir probe
IDP: a particle detector.

The Launcher that will be used is a DNEPR which would be launched from Baikonour with other passengers.