Dynamic modeling and stability analysis of a flexible spinning missile under thrust
Dynamic modeling and stability analysis of a flexible spinning missile under thrust
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DOI：
10.1016/j.ijmecsci.2016.09.027
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发表时间：
2016-12
影响因子：
7.3
通讯作者：
Tian-fu Xu;J. Rong;D. Xiang;Chenglong Pan;Xinzhe Yin
中科院分区：
文献类型：
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作者：
Tian-fu Xu;J. Rong;D. Xiang;Chenglong Pan;Xinzhe Yin
建立了动力飞行阶段柔性自旋导弹在推力作用下的一般运动方程，分析了导弹运动的稳定性。将旋转的导弹近似为无约束柔性旋翼。在平均轴线条件下，考虑陀螺效应、气动弹性效应和轴向力等因素，将动力飞行阶段的推力视为随动载荷。在此基础上，推导了柔性旋转导弹动力飞行阶段的运动方程和稳定性方程。通过数值计算，分析了柔性自旋导弹在推力作用下的稳定性和动态响应。计算结果表明，推力、转速和动压对自旋导弹的稳定性有不同程度的影响。这些因素应该综合考虑和分析。
The general equations of motion of a flexible spinning missile under thrust in the powered flight phase are established and the stability of the motion of the missile is analyzed. The spinning missile is approximated to the unconstrained flexible rotor. Moreover, the thrust in the powered flight phase is deemed as a follower load when the factors of gyroscopic effect, aeroelastic effect, and axial force are considered under the mean axis condition. The equations of motion and stability of the flexible spinning missile in the powered flight phase are then deduced. The stability and dynamic response of the flexible spinning missile under thrust is analyzed through numerical calculation. Calculation results show that thrust, spinning speed, and dynamic pressure exert different influences on the stability of the spinning missile. These factors should be considered and analyzed comprehensively.