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High Thrust Bleed Rocket Engines for a Fly-Back Booster Application

Sippel, M. and Herbertz, A. (2002) High Thrust Bleed Rocket Engines for a Fly-Back Booster Application. In: International Symposium on Propulsion for Space Transportation of the XXIst century, pp. 1-10. 6th International Symposium on Propulsion for Space Transportation of the XXI Century, Palais des Congress, Versailles, France, 14 - 17 May 2002.

Full text not available from this repository.

Abstract

In this paper a high trust, cryogenic bleed cycle engine is analyzed, to be used for propulsion of future reusable booster stages of a heavy lift launcher. Based on results of an earlier cycle analysis, an improved engine variant is investigated. Its performance is calculated, and a preliminary engine sizing and mass analysis is carried out. Improvement options as well as growth potential of the cycle is regarded. Different turbo-pump lay-outs are looked upon to indicate the most promising one. An ascent trajectory optimization and a discussion of the complete vehicle are performed to evaluate the engine as part of a future semi reusable launch system.

Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2002,
Title:High Thrust Bleed Rocket Engines for a Fly-Back Booster Application
Authors:
AuthorsInstitution or Email of Authors
Sippel, M.UNSPECIFIED
Herbertz, A.UNSPECIFIED
Date:2002
Journal or Publication Title:International Symposium on Propulsion for Space Transportation of the XXIst century
Page Range:pp. 1-10
Editors:
EditorsEmail
AAAF, UNSPECIFIED
Status:Published
Event Title:6th International Symposium on Propulsion for Space Transportation of the XXI Century, Palais des Congress, Versailles, France, 14 - 17 May 2002
Organizer:AAAF
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):E -- no assignement
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion
Deposited By: Monika Lohmiller
Deposited On:16 Sep 2005
Last Modified:06 Jan 2010 13:58

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