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• W2322383702 abstract "System studies on a generic vehicle, performed by AEROSPATIALE MATRA, ONERA and DASSAULT AVIATION in the framework of French Research and Technology Program for Advanced Hypersonic Propulsion (PREPHA), have shown how airbreathing propulsion, combined with high performance rocket propulsion, could improve the feasibility of a fully reusable SSTO space launcher. Nevertheless, performance, obtained with the provided technology level and with a fixed-geometry dual-mode ramjet, were not sufficient to allow the use of a landing gear sized to comply with full mass vehicle take-off requirements because of corresponding mass. Since 1993, AEROSPATIALE MATRA Missiles and the Moscow Aviation Institute have been developing the concept of a variable-geometry-dualmode-ramjet called Range and the associated technology demonstration. The considered engine has a fully variable internal geometry which gives it a priori a high performance level over the whole Mach number range. Technology development work led to the design and partial demonstration of materials and structures solutions to comply with the variable geometry requirements. These technologies should be definitively demonstrated thanks to the tests of a large scale prototype in AEROSPATIALE MATRA Missiles Bourges-Subdray Center (connected pipe test up to Mach 6.5 entrance of combustor 212x257 mm). A common work has been realized by AEROSPATIALE MATRAMISSILES and Moscow Aviation Institute to study the adaptation of the WRR engine concept to PREPHA-type generic vehicles. Taking into account the developed technologies, a detailed mass budget has been defined for the airbreathing propulsion system. A simplified but efficient methodology has been developed at AEROSPATIALE MATRAMISSILES to analyze the interest of several propulsion systems on a SSTO of PREPHA-type. WRR has then been compared with other propulsion systems. These results, enhanced year after year, have been presented at the previous Joint Propulsion Conferences in 1998 and in 1999. In particular, the use of a full-scale WRR should allow to design a generic vehicle of PREPHA class, but using a take-off gear, with a 450 tons take-off weight: this point was estimated as non possible for every other fixed engine model. During the current year of common work, studies have been again enhanced and significant technology has paved the way of consolidation of the capacity of realization of such Wide Range Ramjet engines. In particular, the new results from the paper studies give comparison of WRR propelled PREPHA-type vehicle with literature-available propulsion models and other technology assumptions for SSTO. A concern is also the methodology of incremental development and in particular scaling effect and more appropriate experimental vehicles and associated testing methodology. In parallel to these system studies, status of associated technology developmentis described. NOMENCLATURE AMM Aerospatiale Matra Missiles CMZ Common Memory Zone DCT Double Col Thermique ICM Integrated Computational Model FSR Full Scale Ramjet GTP Global Test Program HPE Heat Protective Element MAI Moscow Aviation Institute PCC Prototype Control Code RBCC Rocket Based Combined Cycle SSTO Single Stage to Orbit TOW Take-Off Weight TSTO Two Stage to Orbit WRR Wide Range Ramjet Copyright © 2000 by AEROSPATIALE -MATRA MISSILES and MOSCOW AVIATION INSTITUTE. Published by the American Istitute of Aeronautics and Astronautics, Inc, with permission. -1 American institute of Aeronautics and Astronautics (c)2000 American Institute of Aeronautics & Astronautics or Published with Permission of Author(s) and/or Author(s)' Sponsoring Organization." @default.
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• W2322383702 date "2000-07-24" @default.
• W2322383702 modified "2023-10-18" @default.
• W2322383702 title "Airbreathing space launcher interest of a fully variable geometry propulsion system and corresponding French-Russian partnership" @default.
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• W2322383702 doi "https://doi.org/10.2514/6.2000-3340" @default.
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