Reuse-X Vehicle Approach – A Key Element of FLPP In-flight Technology Experimentation and Demonstration
- Paper number
IAC-06-D2.6.06
- Author
Mr. Herbert Grallert, NGL Co Office, Italy
- Coauthor
Mr. Laurent Bouaziz, Italy
- Year
2006
- Abstract
The elements of the ESA’s Future Launcher Preparatory Program are: system activities, technology developments on materials \& structures, and propulsion systems/ technologies. The overall approach is system-driven, i.e. FLPP aims at defining reference launcher concepts. These were used for deriving a demonstration logic including in-flight experimental vehicles, and technology development requirements. This paper addresses the activities on the Reusability eXperimental Vehicle (dubbed Reuse-X) performed in the first part of the FLPP System Studies which were commenced early in 2005. The major Reuse-X objectives of FLPP were first derived from RLV technology requirements. Reuse-X demonstration objectives are reflecting the complements to on-ground demonstration needs. These demonstration objectives are mainly addressing (1) turnaround cycle experimentation (as a major cost-driver for RLV’s) and (2) in-flight validation of thermo-mechanical design solutions (exposure to combined thermal and mechanical loads). In a second step, several Reuse-X potential candidates (EXTV-2 from FESTIP, Phoenix-2 concepts from EADS-ST, Dassault Aviation’s VEHRA, US X-34) have been reviewed and analyzed whether they would fulfill the demonstration requirements. Finally, only Phoenix-2 variants were found capable to cover the full range of flight domains required for the technology experimentation at representative loads levels. However, in order to meet all of the demonstration objectives, the initial features of Phoenix-2 demonstrator vehicles had to be modified moderately according to a generic aerodynamic shape and a representative launch mode, propulsion system, and thermo-mechanical design. With such modifications, the vehicles would be representative in many respects for the whole variety of different RLV concepts identified in the system study. Two vehicle concepts, one with cryogenic propellants and one with LOX/Kerosene, were analyzed in more details, also taking into account potential design changes. In the third step of the study, a preliminary re-design loop was initiated in FLPP Phase 1 including the update of aerodynamic data basis, CATIA design, review of the propulsion system architecture, thermo-mechanical design of airframe and TPS, mass and performance assessments including controllability, operational procedures and cost assessment. Different measurement methods and sensors were recalled in the review of flight test equipment, and their characteristics were evaluated. A tentative flight test plan was proposed expanding over 2 years with 3 test campaigns and no more than 28 individual missions. This paper develops the different steps of the Reuse-X study and provides the main design and operational characteristics of the two recommended alternatives of the Reuse-X vehicle.
- Abstract document
- Manuscript document
IAC-06-D2.6.06.pdf (🔒 authorized access only).
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