Airbreathing hypersonic propulsion system integration within FESTIP FSSC-12

S. Kopp; S. Hollmeier; H. Rick; O. Herrmann

doi:10.2514/6.1999-4813

Airbreathing hypersonic propulsion system integration within FESTIP FSSC-12

S. Kopp, S. Hollmeier, H. Rick, O. Herrmann

Chair of Turbomachinery and Flight Propulsion

Research output: Contribution to conference › Paper › peer-review

3 Scopus citations

Abstract

This paper presents the first stage of a two-stage-toorbit (TSTO) space transportation system, studied within the European FESTIP-programme, as well as its highly integrated air-breathing propulsion system. Compared to previous design studies (e.g. the former German hypersonic research reference concept “Sanger”) stage separation will be at a relatively low flight Mach number of 4.0. The lower stage is powered on its entire flight by turbo engines with reheat only. Therefore, the use of ramjets together with complex turbo engine closure mechanisms can be avoided. Performance characteristics of the lower stage considerably depend on engine integration and thus on the components air inlet and exhaust nozzle. Within this study a twodimensional ramp inlet with mixed external and internal compression, a single expansion ramp nozzle (SERN) and the performance of the installed turbo engine have been examined in detail.

Original language	English
DOIs	https://doi.org/10.2514/6.1999-4813
State	Published - 1999
Event	9th International Space Planes and Hypersonic Systems and Technologies Conference, 1999 - Norfolk, United States Duration: 1 Nov 1999 → 4 Nov 1999

Conference

Conference	9th International Space Planes and Hypersonic Systems and Technologies Conference, 1999
Country/Territory	United States
City	Norfolk
Period	1/11/99 → 4/11/99

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10.2514/6.1999-4813

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title = "Airbreathing hypersonic propulsion system integration within FESTIP FSSC-12",

abstract = "This paper presents the first stage of a two-stage-toorbit (TSTO) space transportation system, studied within the European FESTIP-programme, as well as its highly integrated air-breathing propulsion system. Compared to previous design studies (e.g. the former German hypersonic research reference concept “Sanger”) stage separation will be at a relatively low flight Mach number of 4.0. The lower stage is powered on its entire flight by turbo engines with reheat only. Therefore, the use of ramjets together with complex turbo engine closure mechanisms can be avoided. Performance characteristics of the lower stage considerably depend on engine integration and thus on the components air inlet and exhaust nozzle. Within this study a twodimensional ramp inlet with mixed external and internal compression, a single expansion ramp nozzle (SERN) and the performance of the installed turbo engine have been examined in detail.",

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AU - Rick, H.

AU - Herrmann, O.

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AB - This paper presents the first stage of a two-stage-toorbit (TSTO) space transportation system, studied within the European FESTIP-programme, as well as its highly integrated air-breathing propulsion system. Compared to previous design studies (e.g. the former German hypersonic research reference concept “Sanger”) stage separation will be at a relatively low flight Mach number of 4.0. The lower stage is powered on its entire flight by turbo engines with reheat only. Therefore, the use of ramjets together with complex turbo engine closure mechanisms can be avoided. Performance characteristics of the lower stage considerably depend on engine integration and thus on the components air inlet and exhaust nozzle. Within this study a twodimensional ramp inlet with mixed external and internal compression, a single expansion ramp nozzle (SERN) and the performance of the installed turbo engine have been examined in detail.

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Airbreathing hypersonic propulsion system integration within FESTIP FSSC-12

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