The Microscope satellite is constituted of:

• a microsatellite platform whose general design is based on the Myriade generic platform but also integrates new equipment and special functions for this mission.
  
  • There is no orbit control with hydrazine thrusters; they are replaced by a set of cold gas microthrusters (nitrogen) set upon four corners of the cubic structure.
  • The attitude control uses the two payload accelerometers and the microthrusters. It is performed together with a new acceleration control function which enables to nullify all the non gravitational components measured by the accelerometers.
  • The solar generator, specially developed for this satellite, is composed of two rigid panels which do not turn because the orientation of the satellite guarantees a permanent pointing toward the Sun, thus avoiding the generation of parasite disturbances for the mission.

• a payload, installed at the centre of the satellite, and formed by:
  
  • A T-SAGE instrument made of two independent SAGE differential accelerometers, each possessing a mechanical module and an electronic control unit, plus a joint electronic unit for the interface with the satellite,
  • A lattice structure equipped with thermal protection which holds the sensitive units and maintains a constant temperature, the Payload Assembly Subsystem.

The whole satellite has a mass of 300 kg with dimensions under the fairing much larger than those of the other Myriade satellites: 1.4 m x 1 m x 1.5 m.

     
Drawings of the satellite with its solar panels deployed and platform opened.

Drawing of the satellite in its end-of-life configuration