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CM Standard Evolution 1

Objectives

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

Challenges

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.

Benefits

CM Std Evo1 design allows to :

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

Features

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

Plan

  • 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

Documentation

Documentation may be requested

Prime Contractor

Contacts

Status date

Wednesday, March 22, 2017 - 09:14

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