固体火箭发动机燃气舵推力损失的数值分析与测试

Numerical and Experimental Analysis on Thrust Loss of Jet Vanes for Solid Rocket Motor

燃气舵是实现推力矢量控制(TVC)的一种方式,但在固体火箭发动机(SRM)尾流工作中的燃气舵不可避免的造成一定程度的推力损失,导致发动机性能下降和导弹射程减小。受发动机推力个体差异和量值小限制,给准确测试和评估推力损失数据带来困难。通过数值仿真方法,五分量天平和六分力测力试验,建立了一套相对实用的测试和分析方法,得到了较为精确的推力损失数据,为燃气舵和导弹总体设计提供了依据。

Jet vane is a way of achieving thrust vector control （TVC）. However, solid rocket motors in the wake of the jet vane work will inevitably cause a degree of thrust loss, this will lead to decline SRM performance and shorten missile range. The limitation of difference of individual SRM thrust value and the small restrictions bring difficult to accurate test and evaluate thrust loss. Through numerical simulation, 5DOF dynamic loads and six force dynamometer test, a practical method of testing and analysis method was established, from which more accurate thrust loss data were obtained, this can be referable to jet vane and missile system design.