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 unguided flight model of missile's initial trajectory is set up based on the 6 degree-of-freedom equation and the simulation is carried out in conjunction with the model of eject power and the model of thrust of engine. Founded on flight model and the results of simulation, the characteristic of ejected launch of missile on UCAV is analyzed, and the separation security and the control of missile attitude during the early flight have been studied. Based on comparative movement analysis of missile under different static stabilities, an appropriate range of missile static stability has been presented according to different security or control requirement. Finally, the optimal static stability that fulfilled all requirements turn up. A case study shows that the model as well as the method is reasonable and effective.
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