ARIANE 5 Upper Composite de-Orbiting Scenario for ATV Jules Verne Mission
- Paper number
IAC-07-D2.3.02
- Author
Mr. Markus Jaeger, EADS Astrium, Germany
- Year
2007
- Abstract
In 2007, the first-ever ATV (Automated Transfer Vehicle) mission, dubbed Jules Verne, envisages to launch the ATV S/C (Spacecraft) with the ARIANE 5 rocket into a 260-km orbit in order to serve the ISS (International Space Station). The ATV mission will only begin when the ATV S/C is jettisoned into a LEO orbit (Low-Earth Orbit) by an ARIANE 5 after the lift-off from the French Guiana equatorial launch site. ATV thrusters are then fired to boost the ATV into the transfer orbit to the ISS. But not only the first flight of the ATV to the ISS is an historic event for the European space community. The ATV mission requires specific also features of the ARIANE 5 launch vehicle such as re-ignition boosts of the ARIANE 5 upper stage EPS (Etage à Propergols Stockables) not only to inject the upper composite into a circularized LEO prior to separation of the ATV S/C but also to de-orbit to Earth the remaining upper composite after the placing of the ATV S/C into LEO. Clearly, the latter must be performed in order not to endanger any human life. This paper presents first the final synthesis of System studies with regard to the nominal deorbitation of the remaining upper composite into the South Pacific Ocean. Provided for the Jules Verne ATV mission, the results will characterize the de-orbiting deltaV budget allowing the localization of the impact footprint of the debris inside the targeted area while complying with fallout constraints. Based on works performed by ASTRIUM-ST with the appreciated cooperation of CNES, the results of the System synthesis are thus issued from a joint effort. Second the specific upper stage studies are summarized for the de-orbiting of the upper composite within the ATV Jules Verne mission as de-pressurization and passivation scenarios of the Propellant Tanks as well as thermal and mechanical verification of structural parts. Finally a general overview of the specific re-ignition qualification program performed for the EPS AESTUS Engine is presented in order to cover changed temperature and pressure flight domains at the moment of Engine re-ignition for the de-orbiting boost.
- Abstract document