Expendable Future European Launcher Options and Technology Preparation

Paper number

IAC-08.D2.4.6

Author

Dr. Martin Sippel, Deutsches Zentrum für Luft und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Arnold van Foreest, Deutsches Zentrum für Luft und Raumfahrt e.V. (DLR), Germany

Coauthor

Mr. Markus Jaeger, Astrium Space Transportation, Germany

Coauthor

Dr. Jens Gerstmann, DLR German Aerospace Center, Germany

Coauthor

Mr. Jean-Phillipe Dutheil, Germany

Year

2008

Abstract

The investigation on the future European options in payload delivery to orbit is going on in different national and multi-national contexts. The range of interest reaches from potential adaptation and rearrangement of existing stages to complete new developments. Payload classes vary between small LEO and heavy GTO capabilities.

The system activities in Germany during the last two years focus on a next generation upper-medium class expendable TSTO and options for new liquid fuel upper stages for the small VEGA-launcher. Two DLR-agency funded studies support the investigations of these subjects [1]: WOTAN on the next generation launchers and VENUS on potential new VEGA upper stages. Beyond that effort technology preparation and maturation activities for re-ignitable cryogenic upper stages are under way. All work is performed as a joint effort of DLR with German launcher companies EADS astrium and MT Aerospace.

The paper describes some of the most recent results in the technical assessment of future European launcher architecture. The WOTAN TSTO concepts with an intended initial operational capability after 2020 are currently resized and refined in a second iteration loop. The obtained mechanical architecture and structural analysis allows identification of technological challenges and checking on the economic viability. A broad range of small launcher upper stages have been investigated in VENUS spanning storable as well as different cryogenic propellants. Based on a comparison of achievable performance and required development effort, the preliminary stage design concentrate on a storable propellant variant with Aestus2 engine and cryogenic LOX-LH2 versions using an adapted VINCI rocket motor. The system investigations in VENUS are not only based on the VEGA solid propellant lower composite currently under final development, but also on its potential more powerful future upgrade.

In its second part the paper gives an overview on advanced cryogenic upper-stage technologies presently under investigation in Germany. A research cooperation of German launcher industry, University academia and DLR has been initiated to work jointly on various identified needs. Key research interests are the propellant management technology under various acceleration and weightlessness conditions, the simulation of the propulsion system together with on-board thrusters, composite fibre structures, and avionics including flight control.


1.	Sippel, M.; van Foreest, A.; Dutheil, J.-P.; Philip, P.: Technical Assessments of Future European Space Transportation Options, IAC-07-D2.7.09, September 2007

Abstract document

IAC-08.D2.4.6.pdf

Manuscript document

IAC-08.D2.4.6.pdf (🔒 authorized access only).

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