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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 analyze the nonlinear free-rolling and rolling stability characteristics of the edge-guided wing missile model, a theoretical analysis combined with the dynamic force measurement test and the free-wheeling degree release test was adopted to simulate the nonlinear behavior of the model 0 ° ~ 60 ° angle of attack within the rolling motion, roll stability characteristics with the angle of attack changes were studied. At 10 ° angle of attack, the model is statically stationary in 4 “+” positions and balanced in roll motion at the “+” position; roll angles greater than 20 ° The static equilibrium position is changed into 4 “×” shape positions; when the angle of attack is 20 °, the model rolls at the position of “X” shape to keep the balance. When the angle of attack is larger than 30 °, the model produces the roll limit Ring self-oscillating motion, the angle of attack reached 60 ° when the model’s divergent divergence evolved into high-speed rotation form. The results show that the form of roll motion depends on the static and dynamic characteristics of roll torque.