火箭基组合循环发动机热结构技术研究进展  

Thermal structure technology development of rocket based combined cycleengine

作　　者：秦飞[1,2] 赵征 何国强 景婷婷[1,2] 孙星 魏祥庚 QIN Fei;ZHAO Zheng;HE Guoqiang;JING Tingting;SUN Xing;WEI Xianggeng(School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China;National Key Laboratoryof Solid Rocket Propulsion,Xi'an 710072,China)

机构地区：[1]西北工业大学航天学院,西安710072 [2]固体推进全国重点实验室,西安710072

出　　处：《航空学报》2024年第11期66-83,共18页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(52106055,52302478)。

摘　　要：宽速域、大空域、高比冲的火箭基组合循环发动机作为实现未来水平起降可重复使用天地往返运输系统、临近空间高速飞行平台等新型空天飞行器的主要动力系统之一,近年在宽域燃烧组织、模态过渡控制、高效热防护等关键技术方面取得了诸多进展,但在发动机热结构技术方面,由于新型空天飞行器要求动力系统工作速域更宽、结构系数更低,而发动机热结构设计面临宽域飞发任务耦合特性强、时空非均匀力热环境复杂、薄壁结构轻量化难度大、多次重复使用等难题,因此,必须一方面通过飞发总体参数匹配研究确定合理的发动机热结构指标约束,另一方面多角度提升发动机热结构设计水平和指标能力边界。首先,将国外以典型火箭基组合循环发动机为动力的空天飞行器作为对象,分析了入轨方式对动力系统热结构指标需求的影响规律,并梳理了GTX、Strutjet两款典型发动机的热防护与热结构方案,进而通过发动机燃烧组织与热环境分布特征分析,介绍了主被动结构热防护、高温结构可变可调、结构重复使用与健康管理三类关键技术的研究进展。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 highefficiency 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 thermalstructure,ispresented.

关 键 词：空天飞行器 火箭基组合循环发动机 主动热防护 轻质热结构 可重复使用 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程] V11