喷口遮挡对射流式姿控火箭发动机性能的影响  

Impact of blocked spouts on the performance of an attitude control rocket motor

作　　者：徐勇[1] 杨树兴[1] 莫波[1] 王玉芳[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《固体火箭技术》2004年第2期101-104,共4页Journal of Solid Rocket Technology

基　　金：跨世纪人才培养计划基金资助。

摘　　要：通过数值模拟和试验研究,分析了喷口遮挡对姿控火箭发动机性能的影响。结果表明,当发动机喷口被遮挡时,姿控发动机不能跟随控制指令产生所需的反向推力,其稳定弹轴的能力减弱,从而影响火箭弹的落点精度。The influence of blocked spout on the performance of attitude control rocket motor was analyzed by numerical simulation and test. The results show that the motor can not generate required reverse thrust consistent to control signal when some spouts of the motor are blocked. When the ability of stabilizing the rocket axis is decreased, the delivery accuracy is reduced.

关 键 词：火箭发动机 姿态控制 数值模拟 推力测量 湍流模式 雷诺应力 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]