Industry Final Reports


This page contains some final reports of closed activities ran by the onboard computer and data handling section of ESTEC. All these documents are public for ESA member states only.
 
2011
  
Title: RF Wireless Intra-Spacecraft Communications
Contract: TRP Contract AO1-533907NLGLC
Contact: Onboard Computer and Data Handling Team
Final Report: ESA member states industrials and academics may request the activity's final report. Please request a password with the contact above.
Summary:
    An Low Power Proximity Network System (LPPNS) has been developed based on initial User Case driven requirements analysis. A full development programme has been undertaken leading initially to a set of demonstration modules which have been successfully tested in three application areas in mock-ups or at test sites:
    • Launcher Applications
    • Spacecraft Applications (in-orbit and during AIV)
    • Planetary science Applications
    An additional LPPNS module has been designed to demonstrate a temperature sensor node in a robust, long lifetime (battery) form factor. This has been successfully tested for vibration and thermal-vacuum.

 
 
 2010
  
Title: Demonstration test bed for efficient on board sensor networks
Contract: TRP Contract 21968/08/NL/AT
Contact: Onboard Computer and Data Handling Team
Final Report: ESA member states industrials and academics may request the activity's final report. Please request a password with the contact above.
Summary:
    The aim of the projects is to define and prototype a solution for telecom spacecraft on board tier 2 sensor networks, and to perform a proof of concept with a resulting demonstrator. The sensor bus technology could offer significant benefits in terms of easier system testing and integration, component re-use, outsourcing of components and a reduction in the harness through a significant decrease in the amount of point to point interfaces.
    The sensor or transducer bus would also remove these simple interfaces from the time critical loops located in the CDMU or RTU. The addition of a sensor bus will create a three tier bus structure in the spacecraft consisting of SpaceWire, a time triggered command and control bus (CAN or 1553) and the transducer bus.

 
 
  
Last update: 4 April 2012