运载火箭发动机喷管变形机构型综合分析研究  

Research on Type Synthesis of the Launch Vehicle Engine Nozzle Morphing Mechanism

作　　者：马红鹏 吴会强 张宏剑 曹熙炜 蒋亮亮 乐晨 MA Hongpeng;WU Huiqiang;ZHANG Hongjian;CAO Xiwei;JIANG Liangliang;YUE Chen(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《宇航总体技术》2023年第4期41-50,共10页Astronautical Systems Engineering Technology

基　　金：中国科协学科发展项目(2019XKFZ02);中国科协青年人才托举工程(2016QNRC001-YESS20160107);中国科协优秀中外青年交流计划(2019293);国家自然科学基金(11402033);中国运载火箭技术研究院青年人才拔尖计划。

摘　　要：为有效缩短箭体长度,增大喷管扩张比,提高发动机比冲,对运载火箭发动机进行了喷管变形机构型综合分析。首先分析了国内外喷管变形机构发展历程,在此基础上系统总结了喷管变形机构的典型应用,并对典型喷管变形机构进行了方案分析,研究了其组成原理和功能设计特点,最后基于机构拓扑图分析方法给出机构构型方案及设计方法。介绍了国内外相关喷管变形机构各构型方案运动原理及设计特点,并综合分析评价了各方案,提出了喷管变形机构技术发展建议,可为运载火箭发动机变形机构设计提供支撑。In order to shorten the length of the rocket body effectively,increase the nozzle expansion ratio,and improve the specific impulse of the engine,a type synthesis analysis of the nozzle morphing mechanism of the launch vehicle engine is carried out in this paper.Firstly,the development history of nozzle morphing mechanism at home and abroad is analyzed,then the typical application of nozzle morphing mechanism is summarized systematically,the scheme of typical nozzle morphing mechanism is analyzed,and its composition principle and functional design characteristics are studied.Finally,the configuration scheme and design method of mechanism are given based on the mechanism topology analysis method.In this paper,motion principle and design characteristics of each configuration scheme of nozzle morphing mechanism at home and abroad are given,and comprehensive analysis and evaluation of each scheme are made,Technical development suggestion of nozzle morphing mechanism is put forward,which can provide support for the design of rocket engine morphing mechanism.

关 键 词：发动机喷管 变形机构 型综合 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]