Satellite

The Picard satellite comprised:

• Spacecraft bus

CNES has developed its Myriade series of microsatellite buses using common systems.
This bus is designed for satellites with a launch mass of around 120 kg. The attitude control system employs a star tracker, Sun trackers, a magnetometer, gyros, magnetic bars and reaction wheels. A hydrazine thruster system is used for stationkeeping and orbital manoeuvres.
Flight management is centralized around a T805 10-MIPS microprocessor. Mass storage is also available for data. Telemetry and telecommands use the CCSDS standard.

• Payload
• SOVAP (SOlar VAriability Picard)
• PREMOS (PREcision MOnitor Sensor)
• SODISM (SOlar Diameter Imager and Surface Mapper)
• PGCU (Picard Gestion de la Charge Utile), payload management unit

 

 

The launch date was dictated by the need to conduct observations during the ascending phase of solar activity (starting in 2010) and by the satellite’s development schedule. The satellite was launched on 15 June 2010 with the Swedish PRISMA satellite on a Russian-Ukrainian Dnepr launcher operated by Kosmotras.