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本文介绍了高性能双脉冲发动机导弹在两种飞行环境中弹道和推进系统同时优化的综合分析法。这一研究采用了具有罚函数的拟牛顿参量优化方法来满足终端和轨迹的约束条件。用分段线性开环指令和分段不变反馈增益将弹道控制变量参量化。要优化的脉冲发动机参数是脉冲宽度、平均推力、中性系数、脉冲燃烧时间和脉冲间的延迟时间等。与采用原来规定的火箭发动机推力数据优化的弹道相比,火箭发动机推力时间曲线与弹道一起优化使射程增加了11％。
This paper presents a comprehensive analysis of simultaneous optimization of ballistic and propulsion systems in two flight environments for high performance dual pulse engine missiles. This study uses a quasi-Newton parameter optimization method with penalty function to satisfy the constraints of the terminal and the trajectory. Ballistic control variables are parameterized with piecewise linear open-loop commands and piecewise constant feedback gains. The pulse engine parameters to be optimized are the pulse width, the average thrust, the neutral coefficient, the pulse burning time and the delay time between pulses. The rocket engine thrust time profile was optimized with the ballistic trajectory to increase the range by 11% over the ballistic trajectory optimized with the original rocket engine thrust data.