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本文采用à(迎角)与 T(推力)作为控制变量分析了战斗机对比例导引导弹的最佳躲避机动。经过初步分析,用急剧爬升法在数值上解出了实际的导弹与目标的非线性运动学问题。结果表明,在两维平面内的最佳躲避机动是垂直的 S 型或半滚倒转的 S 型。最小推力弧主要出现在尾追情况下,并且可以采用最大值原理加以说明。
In this paper, we use à (angle of attack) and T (thrust) as the control variables to analyze the best avoidance maneuver of the fighter pilot missile. After a preliminary analysis, using the steep climb method to solve the actual problem of the nonlinear kinematics of missiles and targets numerically. The results show that the best avoidance maneuver in the two-dimensional plane is the vertical S-shape or the S-shape with semi-convolution. The minimum thrust arc occurs mainly in the tail chase case, and can be described using the maximum principle.