带边条翼导弹滚转稳定性分析

doi:10.7527/S1000-6893.2015.0006

Abstract

Abstract:

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.

Key words: missile, rolling motion, rolling stability, strake wing, releasing of constraint freedom

CLC Number:

V211.12⁺1

GENG Xi, SHI Zhiwei, CHENG Keming, GONG Zheng, LIU Chao. Rolling stability analysis of missile with strake wing[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(10): 3241-3248.

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Rolling stability analysis of missile with strake wing

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