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摘要:
为适应无人自主空战条件下对空空导弹火控解算的特殊需求，提出了基于目标机动预估的空空导弹可发射区问题。首先，基于导弹-目标追逃对抗策略，设计了目标机动预估模型，根据导弹与目标的相对方位信息，实现对目标逃逸机动方式的预估；然后，基于多种实际约束，构建了导弹运动动力学模型；最后，设计了基于黄金分割搜索算法的可发射区边界求解策略，实现对可发射区边界值的快速精确搜索。仿真结果表明，空空导弹对初始位置位于所提出的基于目标机动预估的可发射区内的目标，具有更大的命中概率；该可发射区更加适应近距空战中目标逃逸机动的剧烈态势变化，有利于导弹战术使用性能的充分发挥。
Abstract:In order to satisfy the special requirement for fire control of air-to-air missiles under unmanned air combat conditions, the problem of launchable area of air-to-air missile based on target maneuver estimation is presented. Based on the missile-target tracking escape countermeasure strategy, the target maneuver estimation model is designed. According to the relative position information of the missile and the target, the estimation of the target escape maneuver mode is realized. Based on a variety of practical constraints, a missile dynamics model is constructed. A launchable area boundary solving strategy based on the golden section search strategy is designed to achieve a fast and accurate search for the boundary value of the launchable area. The simulation results show that the air-to-air missile has a greater probability of hitting the target in the launchable area based on the target maneuver estimation proposed in the paper. The presented launchable area is more suitable for the dramatic change of the target escape maneuver in the close air combat, which is beneficial to the full play of the missile tactical performance.
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图 1 某发射时刻攻击机与目标相对位置、角度关系示意
Figure 1. Schematic diagram of relative position and angle between attacker and target at a launch moment
图 3 导弹-目标相对参数示意
Figure 3. Schematic diagram of relative parameters between missile and target
图 4 典型情况下导弹-目标追逃机动仿真轨迹
Figure 4. Simulated tracking and escaping maneuver trajectory between missile and target under typical condition
图 5 基于目标逃逸机动预估的导弹追踪弹道解算逻辑
Figure 5. Missile tracking trajectory calculation logic based on target escape maneuver estimation
图 6 基于目标机动预估的可发射区远边界搜索流程
Figure 6. Far-boundary search flowchart for launchable area based on target maneuver estimation
图 7 不同解算方法在可发射区解算面积上的对比
Figure 7. Comparison of calculated area of launchable area between different algorithms
图 8 侧向迎头条件下导弹-目标追逃机动仿真轨迹
Figure 8. Simulated trajectories of missile-target pursuit- evasion maneuver under lateral head-on condition
图 9 侧向迎头条件下评价函数随时间的变化曲线
Figure 9. Curve of evaluation function over time under lateral head-on condition
图 10 不同运动状态情况下导弹侧向控制过载函数随时间的变化曲线
Figure 10. Curve of missile's lateral control overload function over time under target's different motion conditions
图 11 典型情况下不同形式的2种可发射区对比解算结果
Figure 11. Calculation result of two forms of launchable area under typical condition
表 1 不同运动状态下的导弹可发射距离解算结果
Table 1. Missile launchable interval calculation results under different motion conditions
状态序号 相对状态信息 可发射距离/m aasp_y/(°) aasp_z/(°) aoff_y/(°) aoff_z/(°) γm/(°) 目标保持定常状态 目标执行预估机动 1 0 0 0 0 0 (363.56, 3 054.98) (266.35, 1 499.18) 2 20 15 90 5 10 (890.56, 4 243.23) (1 156.25, 4 141.01) 3 0 0 180 0 0 (1 332.15, 14 712.11) (1 701.59, 5 597.35) 4 0 0 90 0 0 (655.19, 5 564.34) (868.69, 4 573.34) 5 15 5 0 15 －15 (370.84, 3 065.56) (268.04, 2 168.81) 6 25 －5 45 15 8 (320.03, 3 184.17) (261.37, 854.27) 7 12.5 8 56 28 0 (369.03, 3 513.09) (398.98, 2 555.84) 8 －12.5 －20 －56 0 0 (418.72, 3 472.94) (370.15, 956.56) 9 30 0 180 0 0 (1 739.16, 10 879.83) (2 348.19, 5 320.31) 
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表 2 导弹模拟打靶测试结果
Table 2. Results of simulated missile target test
发射区类型 初始状态 可发射距离解算值/m 距离测试值/m 命中次数 命中率/% 整体命中率/% 本文提出的可发射区 状态3 (1 701.59, 5 597.35) 5 486.37 7 92 89.6 1 534.25 10 2 640.83 9 4 329.25 10 2 523.81 10 状态5 (268.04, 2 168.81) 1 051.03 10 82 923.53 7 771.78 10 1 870.68 6 1 568.86 8 ⋮ 目标保持定常状态下的可发射区 状态3 (1 332.15, 14 712.11) 13 321.53 1 20 37.6 6 482.26 4 8 390.38 2 12 357.48 0 9 346.35 3 状态5 (370.84, 3 065.56) 2 247.08 4 34 2 804.65 4 2 958.01 2 3 043.79 2 2 478.651 5 ⋮
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