February 27, 2017


The Myriade-Evolutions bus is designed for a typical 7-year mission, in low orbit ranging from 500 km to 800 km and Sun-synchronous orbit (SSO) for all local time of ascending node (LTAN).

The bus structure is a parallelepiped rectangle with dimensions of 98 x 102 x 58 cm. It is composed of:

  • An interface ring with the launcher, supporting the propulsion module and the rest of the main structure
  • 4 lateral honeycomb panels to accommodate equipment able to be opened out for integration operations
  • 4 aluminium corners to give the structure extra rigidity
  • An upper honeycomb panel to accommodate the payload

A bi-compliant hydrazine and green propellant chemical propulsion module, based on 4 1-N motors, will assure the LEOP operations, operational orbit stationkeeping and de-orbiting at the end of the mission.

The avionics (computers and attitude control system) relies heavily on the avionics of the existing series at Airbus Defence & Space and Thales Alenia Space to maximize synergies across the range of low-orbit satellites.

The power system comprises a solar array made up of two wings, a battery and a new compact power regulation and distribution unit.

These elements are complemented by a new S-band transceiver for TM/TC, as well as a mass memory and a high data rate emitter in X band for the processing of the mission data flux.

These developments are compliant with the French Space Operation Act (FSOA) and cover functions such as end-of-life passivation (notably depressurization of the fuell tank and electrical passivation).

Key figures

Performance offered to payloads:
Mass: 150 kg
Power: 150 W permanent
Pointing: accuracy < 0.035 °
Propulsion: 150 m/s
Mass memory: 512 Gbits to 4 Tbits
High-rate mission telemetry: 180 to 310 Mbits/s
Platform telemetry rate: 625 kbits/s to 1 Mbits/s
Lifetime: 7 years


Volume allocated to the payloads: 820 x 830 x 1010 mm
Configuration of the solar array adaptable to the mission requirements