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Impact of Mission Requirements and Constraints on Conceptual Launch Vehicle Design by M Rahn; U.M Schöttle; E Messerschmid is a Engineering article available to read on EtoBox.

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The objective of this paper is to analyse the impact of mission requirements and constraints on both the optimum vehicle design and the effects on flight path selection for two types of reusable two-stage-to-orbit launch vehicles. The first vehicle type considered provides horizontal take-off and landing capabilities and is intended to be propelled by an airbreathing propulsion system during stage 1 flight. The second vehicle type assumes a vertical launch and is accelerated by a rocket propulsion system during the booster stage ascent flight. The analysis employs a design tool for simultaneous system and mission optimization. It consists of a CAD-based preliminary vehicle design tool, aerodynamic and aerothermodynamic calculation software, flight simulation programs, and a two-level decomposition optimization algorithm enabling simultaneous system and flight optimization. The results to be presented show that the cruise flight requirement for an European launched mission of the airbreathing vehicle results in a loss of 60 % payload mass as compared to a mere accelerated ascent for a near equatorial mission into the same target orbit assuming constant takeoff mass. The strong depen

Who reads Impact of Mission Requirements and Constraints on Conceptual Launch Vehicle Design?

Author

M Rahn; U.M Schöttle; E Messerschmid

Publisher

Elsevier Science; Elsevier ; Elsevier BV (ISSN 1270-9638)

Published

1999

Language

EN

Field

Engineering (Physical Sciences)