D. Preclik, R. Strunz, G. Hagemann, W. Zinner, G. Langel

Rocket propulsion systems belong to the most critical subsystems of a space launch vehicle, being illustrated in this paper by comparing different types of transportation systems. The aspect of reusability is firstly discussed for the Space Shuttle Main Engine (SSME), the only rocket engine in the world that has demonstrated multiple reuses. Initial projections are contrasted against final reusability achievements summarizing three decades of operating this Space Shuttle engine. The discussion is then extended to engines employed on expendable launch vehicles with an operational life requirement typically specifying structural integrities up to 20 cycles (start-ups) and an accumulated burning time of about 6000 sec (Vulcain engine family). Today, this life potential substantially exceeds the duty cycle of an expendable engine. It is actually exploited only during the development and qualification phase of an engine when system reliability is demonstrated on ground test facilities with a reduced number of hardware sets that are subjected to an extended number of test cycles and operation time. The paper will finally evaluate on the logic and effort necessary to qualify a reusable engine for a required reliability and put this result in context of possible cost savings realized from reuse operations over a time span of 25 years.

Deutscher Luft- und Raumfahrtkongress 2010

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

Deutscher Luft- und Raumfahrtkongress Tagungsband - Manuskripte, 2010, 2010, ; S.1033-1041; 2010; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

Bestellbar

2010