ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Thermal structure technology development of rocket based combined cycle engine
Received date: 2023-09-13
Revised date: 2023-11-06
Accepted date: 2024-04-25
Online published: 2024-05-15
Supported by
National Natural Science Foundation of China(52106055)
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.
Fei QIN , Zheng ZHAO , Guoqiang HE , Tingting JING , Xing SUN , Xianggeng WEI . Thermal structure technology development of rocket based combined cycle engine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(11) : 529572 -529572 . DOI: 10.7527/S1000-6893.2024.29572
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