CAJ | 학술논문

分析了助推-滑翔导弹助推段关机参数要求，并基于牛顿迭代法和正交实验设计求解了助推弹道。牛顿迭代法局部搜索效率高，但易陷入局部最优，为避免初值设置不当导致无法求取可行解，分析了各控制变量的取值范围，并对其划分水平设计正交实验，从每一个正交实验点开始搜索，避免陷入局部最优。仿真结果表明，该方法能够快速求解出满足约束要求的助推弹道。
분석료조추-활상도탄조추단관궤삼수요구，병기우우돈질대법화정교실험설계구해료조추탄도。우돈질대법국부수색효솔고，단역함입국부최우，위피면초치설치불당도치무법구취가행해，분석료각공제변량적취치범위，병대기화분수평설계정교실험，종매일개정교실험점개시수색，피면함입국부최우。방진결과표명，해방법능구쾌속구해출만족약속요구적조추탄도。
In this paper, the requirements of boost-glide missile during boost phase were analyzed and the boost trajectory was gained based on Newton's iterative method and orthogonal experimental design. Newton's iterative method has a high efficiency in local search, but it is sensitive to initial value and easy to fall into local minimum. In this paper, the scope of the control variables was analyzed and the orthogonal experiment was designed by dividing control variables into several levels. The optimal value was searched from each experimental point to guarantee a feasible solution. The simulation result shows that the boost trajectory with constraints could be gained quickly by this method.