北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (8): 1594-1601.doi: 10.13700/j.bh.1001-5965.2016.0567

• 论文 • 上一篇    下一篇

考虑机动效率的多约束导引律设计

王超伦, 薛林, 闫晓勇   

  1. 中国航天科工二院, 北京 100854
  • 收稿日期:2016-07-05 修回日期:2016-08-10 出版日期:2017-08-20 发布日期:2016-10-18
  • 通讯作者: 薛林 E-mail:majie283@sina.com
  • 作者简介:王超伦,男,博士研究生。主要研究方向:弹道设计、制导律设计;薛林,男,研究员,博士生导师。主要研究方向:导弹总体。
  • 基金资助:
    国家自然科学基金(11202023)

Design of guidance law with multiple constraints considering maneuvering efficiency

WANG Chaolun, XUE Lin, YAN Xiaoyong   

  1. The Second Academy of China Aerospace Science & Industry Corp., Beijing 100854, China
  • Received:2016-07-05 Revised:2016-08-10 Online:2017-08-20 Published:2016-10-18
  • Supported by:
    National Natural Science Foundation of China (11202023)

摘要: 针对考虑交会角约束的导引律在可用过载不足时将导致大的交会角误差问题,推导一种考虑时变过载约束的制导形式,而该导引律在实现较大机动的同时会带来较大能量损失,进而提出一种考虑导弹机动效率的多约束导引律。首先,应用最优二次型原理推导出一种时变控制项权系数的闭环制导形式;其次,将导弹机动时刻阻力系数引入时变权系数,并通过迭代分别确定可用过载与机动效率约束边界;最后,将时变过载约束表示成剩余时间的函数,代入制导指令,并进行弹道仿真。结果表明:推导的2种导引律均能较好地实现末端弹道成型要求,考虑机动效率的制导指令分配更为合理,并有效降低了拦截末端速度损耗,提高了制导精度与毁伤效果;且考虑机动效率的导引律中时变权系数无须配平求解,在保证精度的同时极大提高了迭代速度。

关键词: 防空导弹, 导引律, 末端交会角, 多约束条件, 最优控制, 机动效率

Abstract: Due to the guidance law with terminal intercept angle which will cause big angle error when available payload is insufficient, a guidance law considering time-varying overload constraint has been elicited, which would bring on more energy loss when much maneuver is achieved at the same time. Given this, this paper elicits a guidance law with multiple constraints considering maneuvering efficiency. First, a closed-loop guidance law with time-varying control weight coefficient is elicited according to optimal quadratic theory. Second, drag coefficient when maneuvering is introduced into time-varying control weight coefficient, and the constraint boundaries of available payload and maneuvering efficiency are obtained through iterations. Finally, the time-varying weight coefficient is changed into function of time-to-go, and the trajectories are simulated with guidance law considering available payload and maneuvering efficiency. The simulation results indicate that both the two guidance laws can meet the requirement of trajectory shaping, and the acceleration command of guidance law with constraint considering maneuvering efficiency is more reasonable, which reduces the velocity loss effectively and enhances the guidance accuracy and damage effect. Moreover, balance solution of time-varying weight coefficient is not necessary with this method, so iteration speed will be highly improved when accuracy is guaranteed.

Key words: air-defense missile, guidance law, terminal intercept angle, multiple constraints, optimal control, maneuvering efficiency

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