22–24 Oct 2013
European Space Research and Technology Centre (ESTEC)
Europe/Amsterdam timezone

CAN in Space applications - Use of CAN Bus in the VEGA Launcher Autonomous Telemetry Systems.

23 Oct 2013, 12:00
20m
Newton (European Space Research and Technology Centre (ESTEC))

Newton

European Space Research and Technology Centre (ESTEC)

Keplerlaan 1 2201AZ Noordwijk ZH The Netherlands
CAN Bus in Space (22 October PM & 23 October AM) CAN bus in Space - Session 2

Speaker

Mr Francesco Ortix (Temis)

Description

The suite of CAN bus and protocols has been developed to create a reliable, safety critical, deterministic time communication over automotive electronic box use for the complete management of stock cars. It has been demonstrated over time and by widespread diffusion on automotive market the effectiveness and efficiency of CAN protocol and electrical bus on safety critical systems (ABS management, AIRBAG management, engine control, etc.). Basing on this set of protocols TEMIS, thanks to the know-how acquired over 10 years of experience in the automotive CAN application and in Fomula1 cars, has selected a particular protocol over CAN (CAN Calibration Protocol or CCP) to develop an high configurable, modular acquisition and telemetry subsystem for avionic application. The CAN bus has been used for intra-board communication in the processing unit and for critical communication between ground segment and processing unit itself. Two configurations of such telemetry system have flown in the first and second VEGA flight (VV01, VV02) carrying video data, high bandwidth sensor acquisition, IMU acquisition, GPS acquisition preventing radio. The two systems, docked on the upper stage of VEGA launcher, communicated until lift-off via umbilical CAN connection of about 80 meters to the relevant EGSE (positioned in bunker under launch pad). The main functionalities achieved via CAN bus on the system goes from data handling timeline management to ultra fine timestamp of acquisition and events, including update and monitoring of system parameters even when integrated in launch pad. The test and validation of this CAN bus application has been performed using third party commercial COTS to gain low cost of development and fast time of production of EGSE/Test Equipment. Custom software has been developed to support the operations and test over the entire system. The flight data after the two missions reports that all internal communication of on-board system has been correctly performed over entire mission.

Presentation materials