非同轴式喉栓变推力发动机压强响应分析  

Analysis on response of pressure in non-coaxial variable thrust pintle motor

作　　者：魏祥庚[1] 何国强[1] 李江[1] 周战锋[1] 

机构地区：[1]西北工业大学燃烧流动与热结构国家级重点实验室,西安710072

出　　处：《固体火箭技术》2009年第4期409-412,共4页Journal of Solid Rocket Technology

摘　　要：设计了非同轴式喉栓固体变推力发动机实验系统,进行了变推力原理性实验。通过对发动机自由容积、喉栓运动、气缸能否一次完全将喉栓送到位、等效喉部结构、推进剂配方对变推力过程中压强响应影响的实验及分析,基本确定了压强响应慢是由于推进剂的动态响应慢造成的。利用成熟配方的低压强指数推进剂进行了压强双峰响应实验研究。研究结果表明,压强峰的下降响应要高于上升响应。研究结果为非同轴喉栓变推力发动机响应特性分析提供了依据。In order to analyze the performance of variable thrust pintle solid rocket motors, an experimental system of non-coaxial pintle solid rocket motor was designed, and through this system, experiments that validate variable thrust principle were carried out. The pressure curve of the principle experiment shows that the change of pressure was accomplished perfectly during the experi- ment and the transition from low pressure to high pressure was realized. Afterwards, further experimental researches were done so as to find the motor free volume ,pintle movement state, equivalent throat structure, and the influence of propellant composition on the response of pressure during the change of thrust and whether the pintle can be positioned with single action or not. The results show that the response time of propellant is the primary factor which effects the response of pressure. The experiment concerning dual pressure peak was carried out using the proven low pressure exponent propellant. The results show that the rate of the pressure drop is much faster than the rate of the pressure build-up. The conclusion may provides a reference for analysis on response of pressure in non-coaxial variable thrust pintle motor.

关 键 词：固体火箭发动机 推力调节 实验 喉栓 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]