CNES developed a MYRIADE series of microsatellite using as much as possible common equipments.
This platform was designed for a total mass of about 120 kg mass at launch. Its attitude in space is maintained by using a star sensor, solar sensors, a magnetometer, gyrometers, several magnetic rods and reaction wheels. If an orbit control and orbit manoeuvres are needed, a hydrazine system may be used.
The on-board management is centralised, and uses a 10 MIPS microprocessor T805. A mass memory is available for the data storage. The telemetry and telecommand use CCSDS standard.
a payload constituted of four units:
SODISM SOlar Diameter Imager and Surface Mapper,
SOVAP SOlar VAriability Picard,
PREMOS PREcision MOnitor Sensor,
PGCU (PICARD Gestion Charge Utile).
The launch date is constrained by the necessity to realize the observations during the ascending solar activity (beginning in 2010) and by the satellite development calendar, which lead to a launch on June 15, 2010, in dual launch with the Swedish satellite PRISMA, by a Russo Ukrainian launcher DNEPR operated by Kosmotras.