带边条翼导弹滚转稳定性分析

Rolling stability analysis of missile with strake wing

为了分析带边条翼导弹模型的非线性自由滚转运动及滚转稳定特性,采用理论分析与动态测力试验、滚转自由度释放测量试验相结合的方式,对低速来流条件下模型0°~60°迎角范围内的滚转运动、滚转稳定特性随迎角变化的规律进行了研究。在10°迎角时,模型在4个＂＋＂形位置是滚转静稳定的并且在＂＋＂形位置上滚转运动保持平衡;迎角大于20°的范围内滚转静稳定的平衡位置变到4个＂×＂形位置上;并且迎角为20°时模型在＂×＂形位置滚转保持平衡,迎角大于30°后模型产生滚转极限环自激振荡运动,迎角达到60°时模型的滚转运动发散演变为高速旋转的形式。研究结果表明：模型滚转运动的形式决定于滚转力矩的静、动稳定特性。

In order to study the nonlinear free rolling motion and rolling stability of a missile mounted with strake wing,different methods are used including the theoretical method,the dynamic force tests and the free-to-roll measurement.The free rolling motion and the changing of the rolling stability have been studied from the angle of attack（AOA）from 0°to 60°under the low speed free stream condition.At AOA of 10°the rolling statically stable positions are where the model looks like＂＋＂shape and the model can keep stable at these positions after being released rolling free.When the angle of attack is higher than 20°,the rolling statically stable positions have changed to where the model is＂×＂shaped.And at AOA of 20°the model can keep rolling stable at the position where the model is＂×＂shaped.When the AOA is higher than 30°,the model generates the limit cycle oscillation itself at the positions where the model is＂×＂shaped.When the AOA reaches 60°,the rolling motion becomes spinning after the limit cycle oscillation diverges.The results indicate that the rolling motions are determined by the static and dynamic stability of rolling moment.