固体火箭发动机斜切喷管性能影响因素分析  

Influence Factor Analysis of Scarfed Nozzle Performance of SRM

作　　者：刘沛 赵昆 李耿 冯晓柏 LIU Pei;ZHAO Kun;LI Geng;FENG Xiaobai(National Key Laboratory of Combustion,Thermo-structure and Flow,Xi’an Aerospace Propulsion Technology Institute,Xi’an 710025,China)

机构地区：[1]西安航天动力技术研究所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安710025

出　　处：《弹箭与制导学报》2020年第4期140-144,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为获取结构参数对斜切喷管性能的影响规律,采用数值仿真方法对不同结构参数斜切喷管性能进行了对比分析。计算结果表明:采用单锥斜切喷管的发动机,发动机推力随喷管扩张半角的增大而增大,随喷管斜切角和偏置角的增大而减小;采用两段锥斜切喷管的发动机,出口扩张半角增大,发动机推力先增大后基本保持不变。在两段锥斜切喷管设计中,较大的出口扩张半角有利于获得较大的发动机推力,但会造成初始扩张半角减小而加剧烧蚀。In order to obtain the influence law of different structural parameters on the performance of the scarfed nozzle,performance of the scarfed nozzle with different structural parameters was obtained by numerical simulations and compared.The results show that for motor using a single-stage scarfed nozzle,the motor thrust increases with the increase of the divergent half-angle of the nozzle,and decreases with the increase of the scarfed angle and the shaft angle between nozzle and motor axis.For the motor using a two-stage scarfed nozzle,the outlet half-angle of divergent section increases,the engine thrust firstly increases and then remains basically unchanged.In the design of two-stage scarfed nozzle,the larger outlet half-angle of divergent section is beneficial to obtain a larger motor thrust,but it will lead to a smaller inlet half-angle of divergent section which will aggravate ablation.

关 键 词：影响规律 数值仿真 斜切喷管 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]