PAGE CONTENTS
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.
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
