PAGE CONTENTS
Objectives
The purpose of the development is to extend the range of the SPACEBUS™4000C platform family to accommodate payloads up to 14 kW consumption and/or 1 ton dry mass.
Challenges
The key issues related mainly in the two main developments of SPACEBUS Performance:
- The introduction of hybrid propulsion
- The introduction of an innovative Communication Module concept able to support capacitive HTS payloads
System Architecture
The system architecture includes
- Hybrid propulsion: chemical and electrical
- a new Communication Module concept, adapted to current High Throughput Systems (HTS) and flexible payloads
Plan
The project plan has followed classical approach of space development:
- PDR preparation to show feasibility of the architecture and freeze subassemblies specifications
- CDR preparation to perform detailed design and deliver the final justification data pack.
During these phases, not only satellite engineering, but also production and validation processes have been set-up, the overall platform performance has also been assessed.
Finally the SPACEBUS performance SM evolution 1 has been produced and qualified through its first application program, including satellite PFM testing.
Current Status
Completion of CDR in August 2014 has shown a ready to use SM evolution 1 design file and justification file with easily scalable power and mass capability. The first application program has offered the opportunity to qualify the platform through a PFM approach.
The project has been completed with the successful Final Review held in April 2017.
The PFM satellite is a SPACEBUS™4000C4 embarking a 12,6 kW / 747 kg payload. The satellite is to be launched in 2017.
