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Publishing Language: Chinese

Thermal structure technology development of rocket based combined cycle engine

Fei QIN1,2, Zheng ZHAO1,2, Guoqiang HE1,2, Tingting JING1,2( ), Xing SUN1,2, Xianggeng WEI1,2
School of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China
National Key Laboratory of Solid Rocket Propulsion, Xi’an 710072, China
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Abstract

As one of the principal propulsion systems for the development of future horizontal take-off and landing reusable earth-to-orbit transportation systems and near-space high-speed flight platforms, the rocket based combined cycle engine with a broad speed range, extensive altitude range, and high specific impulse has made considerable progress in the key technologies such as wide-area combustion organization, mode transition control, and high-efficiency thermal protection in recent years. However, in terms of engine thermal structure technology, the future aerospace vehicle is required to work in a wider speed range and lower structural coefficient, which places significant challenges on the engine thermal structure design, as the issues such as the strong coupling characteristics of integrated flight and propulsion systems, complex spatial and temporal non-uniform thermal environments, ultra-light weight reduction, and reuse and health monitoring can be encountered. Thus, it is essential to ascertain the optimal engine thermal structure constraints through the investigation of the overall parameters, and enhance the engine thermal structure design capability through various technologies. This paper initially considers the typical foreign rocket based combined cycle engine-powered space vehicles, and analyses the influence of the orbiting mode on the thermal structure index demand of the propulsion system. Then the thermal protection and thermal structure schemes of the GTX and Strutjet engines are examined. Finally the characteristics of the combustion organization of the engine and the distribution of the thermal environment are analyzed, and the research progress of three key technologies, namely, active-passive structure thermal protection, geometrical variable high temperature structure, and reusable thermal structure, is presented.

Keywords

earth-to-orbit aerospace vehiclerocket based combined cycle engineactive thermal protectionlightweight thermal structurereusability
CLC number: V438; V11 Document code: A

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Acta Aeronautica et Astronautica Sinica
Volume 45 Issue 11,
June 2024
Article number: 529572
DOI: 10.7527/S1000-6893.2024.29572
Cite this article:
QIN F, ZHAO Z, HE G, et al. Thermal structure technology development of rocket based combined cycle engine. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529572. https://doi.org/10.7527/S1000-6893.2024.29572

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Received: 13 September 2023
Revised: 06 November 2023
Accepted: 25 April 2024
Published: 17 May 2024
© 2024 The Journal of Acta Aeronautica et Astronautica Sinica
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