Versatility of the ARIANE 5 launch system

Paper number

IAC-08.D2.1.7

Author

Mr. Christian Dujarric, European Space Agency (ESA), France

Coauthor

Mr. Toni Tolker -Nielsen, European Space Agency (ESA), France

Coauthor

Mr. Bernard Chemoul, Centre National d'Etudes Spatiales (CNES), France

Coauthor

Mr. Pascal Noir, Centre National d'Etudes Spatiales (CNES), France

Year

2008

Abstract

The ARIANE 5 launch system consists of two configurations of the launch vehicle; Ariane-5 ECA, the GTO workhorse and Ariane-5, ES, which has proven its versatility, i.e. multiple boost capacity, in the context of the ATV launch on the 9th of March 2008.

The Ariane-5 ECA and Ariane-5 ES have identical lower composites consisting of the cryogenic main stage using the Vulcain 2 engine and the two Solid Rocket Boosters. The differences between the two versions is the upper stage, where the ECA version has cryogenic upper stage based on the HM7 engine and the ES version has a re-ignitable storable propellant upper stage using the Aestus engine.

This paper will present the technical details around the Ariane 5 ES ATV Jules Verne mission and possible new missions to LEO, MEO, and escape with the Ariane 5 ES, exploiting the multi boost capability. Furthermore, activities to   develop a new upper stage for the Ariane-5 ECA with increased GTO performances and re-ignition capability based on the Vinci cryogenic upper stage engine is ongoing and will be the subject of a programme proposal at the ESA Ministerial Council in November 2008.

Abstract document

IAC-08.D2.1.7.pdf

Manuscript document

IAC-08.D2.1.7.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.