固体火箭发动机燃气导流片导转特性分析研究  

The Research on the Guide Characteristics of Solid Rocket Motor Gas Deflector Plate

作　　者：孙钟阜 郑健[2] 薛海峰[2] 

机构地区：[1]海军驻上海地区水声导航军代室,上海201108 [2]南京理工大学机械工程学院,南京210094

出　　处：《弹箭与制导学报》2012年第6期109-111,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：在固体火箭发动机喷管内采用燃气导流片技术,可以使火箭绕其纵轴旋转。文中建立了喷管内燃气导流片流场数值分析的数学和物理模型,通过数值仿真分析了导流片产生导转力矩的原因及其结构参数对火箭导转特性的影响,并采用高速旋转试验和外弹道飞行测试试验结果与理论计算结果进行比较,结果表明火箭最大转速的理论计算结果和试验结果一致性较好,从而验证了燃气导流片数值模型的可靠性。The gas deflector plate in the solid rocket motor nozzle can make rocket rotate around its vertical axis.The mathematical and physical models of gas deflector plate flow field in the nozzle were established in this paper.The reason of steering moment generated by the deflector and the effect of its structure parameters on rocket guide properties were analyzed using numerical simulationm,and the high-speed rotation test and the exterior ballistic test results were compared with the theoretical results.The results show that the calculation results and experimental ones of the maximum speed of the rocket are in good agreement.The numerical model reliability of the gas deflector plate was verified.

关 键 词：固体火箭发动机 导流片 燃气 转速 导转力矩 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]