May 15, 2017


Vue d'artiste de DEMETER au-dessus de la Grèce, notamment du golfe de Corynthe. Crédits : CNES novembre 2003, ill. D. Ducros

The Demeter satellite comprised:

  • The micro-satellite platform with basic instruments. This bus was designed for satellites with a launch mass of about 100 kg. Its attitude control systems included a star tracker, gyrometers, and reaction wheels. It used hydrazine for station keeping. Centralised on-board management was built around a 10 MIPS T805 processor. A mass storage module was available for data storage. Telemetry and remote controls used the CCSDS standard.

  • The payload, comprising technological elements and scientific elements:
    • Technological elements:

      • an 8 Gb mass storage unit,
      • high-speed telemetry (THD),
      • the COA-GPS experiment (GPS Autonomous Orbit Control),
      • the pyrotechnical system photonic initiation line (PYROLASER),
      • the thermal control coating qualification (THERME).

    • Scientific elements:

      • IMSC, a tri-axis set of 3 magnetic sensors (search coils),
      • ICE, a set of 4 electric sensors,
      • IAP, a plasma analyser,
      • ISL, a Langmuir probe,
      • IDP: a particle detector.

DNEPR LauncherDemeter was launched from Baikonur cosmodrome, using a DNEPR launcher carrying other passengers.