European Space Agency

CM Standard Evolution 1


In the frame of SpacebusTM competitiveness project, the CM Standard Evolution 1 development objective are:

Primary targets:

-       To reduce the recurrent and non-recurrent specific costs

-       To improve the flexibility of the SPACEBUS™ 4000C platform concerning the accommodation and the evolution of the payload and consequently to reduce the duration of the accommodation phase at the beginning of the project.

Secondary targets are :

-       To freeze technical inputs (embedded heat pipe network, north/south thermal coupling,  DC harness “main roads”, partial heater accommodation) and drivers (thermal and structural rules) at the program kick off in order to have a platform design less dependent of the payload.

-       To accommodate dissipative units on earth panels

-       To have generic definition for :

  • North/south CM panels for each SPACEBUS™ 4000Ci : raw panels and structural inserts
  • Embedded heat pipes : raw and machined levels and location inside the panels
  • North/south thermal coupling : raw level and location on the panels
  • Earth decks :
    • Lower earth deck : machined level and structural inserts
    • Upper earth deck : raw level and structural inserts

-       To have robust structural design justification files for each SPACEBUSTM 4000Ci consistent with the lateral antenna workshop layout (other ARTES project).

-       To have a thermal analyses allowing to calculate the thermal performances, to define the accommodation drivers applicable to the repeater and to develop a pre-sizing tool for BID phase up to PDR.

-       To define a new concept of satellite handling (lighter and safer)

CM Std Evo1 – thermal mock-up


Main challenges of this project are :

  • To guarantee a thermal performance equivalent to the previous design (only external HP network) while increasing the payload unit accommodation flexibility.
  • To reduce the Non Reccurent activities using standard definitions.
  • To simplify BID phase and PDR thermal analysis using a efficient pre-sizing tool.


CM Std Evo1 design allows to :

  • Reduce global payload accommodation phase and manufacturing schedule
  • Improve competitiveness and cost of SPACEBUSTM 4000C communication module


CM Std Evo1 key features are :

  • Thermal control of the payload performed with only one thermal zone (previously 2 distinct area)
  • 2 kind of raw panels dedicated to radiative or conductive TWT
  • Generic embedded heat pipes network compliant with all standard repeater RF units (C, Ku, Ka, …)
  • External heat pipes for crossing.
  • Generic north/South thermal coupling (performed with external HP).
  • Pre-sizing tool used from bid to PDR to validate the accommodation and the performances earlier in the design


  • Preliminary design and feasibility phase
  • Component and sub-assemblies definition and specification
  • Qualification plan
    • Embedded HP profil
    • Thermal filler          
    • Mechanical and thermal qualification coupon
    • Extension of temperature qualification range of inserts
    • Satellite Handling bracket
  • Critical design review
  • Application on a first program

Current status

Project CDR achieved in March 2014

Project FR achieved in September 2016

Applied on two commercial satellite programs

Status date

Wednesday, March 22, 2017 - 09:14