| 引用本文: | 王超伦,薛林,闫晓勇.考虑弹体动态特性的机动效率约束导引律.[J].国防科技大学学报,2017,39(4):48-55.[点击复制] |
| WANG Chaolun,XUE Lin,YAN Xiaoyong.Guidance law with maneuvering efficiency constraint considering missile dynamic characteristics[J].Journal of National University of Defense Technology,2017,39(4):48-55[点击复制] |
|
| |
|
|
| 本文已被：浏览 8364次 下载 6070次 |
| 考虑弹体动态特性的机动效率约束导引律 |
| 王超伦, 薛林, 闫晓勇 |
|
(中国航天科工二院， 北京 100039)
|
| 摘要: |
| 针对考虑交会角和过载约束导引律在大机动时能量损失大的问题，提出一种考虑导弹机动效率的多约束制导律。应用最优二次型原理推导出考虑一阶弹体延迟的时变导引系数闭环次优制导形式，将导弹机动时刻阻力系数引入时变权系数，并通过迭代确定机动效率约束边界。将时变约束表示成剩余时间与弹体延迟时间的函数，代入制导指令，进行弹道仿真。结果表明，对于常值与机动目标，文中制导律与过载约束导引律同只考虑交会角约束的导引律相比，对目标均能实现末端弹道成型要求，而考虑机动效率的制导指令分配更为合理，在避免指令加速度饱和的同时有效降低了拦截末端速度损耗，提高制导精度与毁伤效果。且该制导律中时变权系数无须配平求解，在保证精度的同时极大地提高了迭代速度。 |
| 关键词: 防空导弹 制导律 动态特性 多约束条件 最优控制 机动效率 |
| DOI：10.11887/j.cn.201704008 |
| 投稿日期：2016-08-23 |
| 基金项目:国家自然科学基金资助项目（11202023） |
|
| Guidance law with maneuvering efficiency constraint considering missile dynamic characteristics |
| WANG Chaolun, XUE Lin, YAN Xiaoyong |
|
(The Second Academy of China Aerospace Science & Industry Corporation, Beijing 100039， China)
|
| Abstract: |
| Due to the guidance law with terminal intercept angle and payload constraints which can cause big engorge loss, a guidance law considering maneuvering efficiency constraint was proposed. A closed-loop sub-optimum guidance law with time-varying control weight coefficient considering first-order missile dynamic characteristics was elicited according to the optimal quadratic theory; The drag coefficient was introduced into the time-varying control weight coefficient, and the constraint boundary of maneuvering efficiency through iterations was obtained; the time-varying weight coefficient was changed into function of time-to-go and delay time, and the trajectories with guidance law considering maneuvering efficiency was emulated. Results indicate that, for constant velocity and maneuvering target, the new guidance law and the guidance law with payload constraint can meet the requirement of trajectory shaping when compared with the guidance law with intercept angle, and the acceleration command of guidance law with constraint considering maneuvering is more reasonable. And the new guidance law can reduce the velocity loss and avoid the payload saturation at the same time, and enhance the guidance accuracy and damage effect. Moreover, it is not necessary to balance solutions of time-varying weight coefficient, so the iteration speed will be improved when accuracy is guaranteed. |
| Keywords: air-defense missile guidance law dynamic characteristics multiple constraints optimal control maneuvering efficiency |
|
|
