Satellite

The Microscope satellite is composed of:

• a microsatellite platform whose overall design is based on the Myriade generic spacecraft bus incorporating new equipment and special functions for this mission.
  
  • For orbit control, hydrazine thrusters are replaced by a set of cold gas (nitrogen) microthrusters at each corner of the cubic structure.
  • Attitude control is achieved with the two payload accelerometers and the microthrusters, together with a new acceleration control function that cancels out all non-gravitational components measured by the accelerometers.
  • The solar array, specially developed for this satellite, is composed of two rigid panels which do not turn because the orientation of the satellite keeps them permanently pointed at the Sun, thus avoiding parasitic disturbances.
  • A de-orbitation system consisting of two deployable booms. By increasing the satellite’s effective surface area and therefore drag, this system guarantees that it will be de-orbited in less than 25 years, in line with the French Space Operations Act (FSOA).

 

 

• a payload, mounted at the centre of the satellite, consisting of:
  
  • a T-SAGE instrument comprising two independent SAGE differential accelerometers, each with 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 supports the sensitive units and maintains a constant temperature: the Payload Assembly Subsystem

The whole satellite has a mass of 300 kg and is much larger than 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, with both booms deployed