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通过刚体飞行六自由度动力学方程建立弹射式导弹初始段无控飞行模型,并结合弹射装置动力模型和导弹发动机推力模型进行仿真计算。基于无控飞行模型和仿真结果分析了无人机配载弹射式导弹发射特性,在导弹初始飞行段对机弹分离安全性和导弹姿态控制要求进行了研究。对导弹不同静稳定度下的运动特性对比分析,分别给出了满足各种安全和控制要求的导弹静稳定度范围。进一步综合所有安全和姿态控制要求,得到了满足所有要求的最佳静稳定度。经过一个实例的仿真研究,结果表明建立的模型与所用到的方法是合理有效的。
The initial flightless missile model of the projectile missile was established by six-degree-of-freedom kinematic equation of rigid body flying, and the simulation was performed by combining the projectile power model and the missile engine thrust model. Based on the uncontrolled flight model and the simulation results, the launching characteristics of the UAV loaded with projectile missiles are analyzed. The safety of the projectile separation and the attitude control requirements of the missile are studied in the initial flight stage of the missile. The comparative analysis of the movement characteristics under different static stability of the missile gives the static stability range of the missile meeting various safety and control requirements respectively. Further consolidating all safety and attitude control requirements, the best static stability is achieved for all requirements. After an example of the simulation study, the results show that the established model and the method used is reasonable and effective.