北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (10): 1980-1986.doi: 10.13700/j.bh.1001-5965.2016.0782

• 论文 • 上一篇    下一篇

基于速度预测的导引律剩余时间估计

张友安1, 梁勇2, 刘京茂3, 孙玉梅1   

  1. 1. 烟台南山学院 电气与电子工程系, 烟台 265713;
    2. 海军航空工程学院 控制工程系, 烟台 264001;
    3. 山东南山国际飞行有限公司, 烟台 265713
  • 收稿日期:2016-10-10 修回日期:2016-12-23 出版日期:2017-10-20 发布日期:2017-01-11
  • 通讯作者: 梁勇 E-mail:ytliangyong@sina.com
  • 作者简介:张友安,男,博士,教授。主要研究方向:先进控制理论与应用,飞行器导航、制导与控制;梁勇,男,博士,副教授。主要研究方向:先进滤波理论与应用,飞行器导航、制导与控制。
  • 基金资助:
    国家自然科学基金(61273058);中国博士后科学基金(20100471796)

Time-to-go estimation for guidance laws based on velocity prediction

ZHANG Youan1, LIANG Yong2, LIU Jingmao3, SUN Yumei1   

  1. 1. Department of Electrical and Electronic Engineering, Yantai Nanshan University, Yantai 265713, China;
    2. Department of Control Engineering, Naval Aeronautical and Astronautical University, Yantai 264001, China;
    3. Shandong Nanshan International Flight Co., Ltd., Yantai 265713, China
  • Received:2016-10-10 Revised:2016-12-23 Online:2017-10-20 Published:2017-01-11

摘要: 将分段线性逼近与迭代求解的思想扩展到对导弹的时变速度进行分段预测,给出了适用于反舰导弹速度时变情况的大前置角下比例导引律和偏置比例导引律的剩余时间估计算法。该算法在现有分段迭代算法的基础上,依据闭环形式的反舰导弹速度微分方程,分转弯平飞段和近似直线飞行段2种情况,对导弹未来速度的大小进行分段迭代预测并对剩余时间估计进行修正。算法中还给出了偏置比例导引律作用下近似直线飞行段剩余飞行航程的估计公式。仿真结果验证了本文算法的有效性。

关键词: 比例导引, 偏置比例导引, 剩余时间估计, 前置角, 攻击时间控制, 反舰导弹, 速度时变, 速度预测

Abstract: The idea of piecewise linear approximation and piecewise iterations is extended to the anti-ship missile’s piecewise velocity prediction. Time-to-go estimation algorithms suitable for anti-ship missiles with time varying velocity are designed for proportional navigation guidance law and a biased proportional navigation guidance law with impact angle control both in the case of large lead angle. The proposed time-to-go estimation algorithms, which are based on the anti-ship missiles’ differential equation of velocity in closed form and the current piecewise-iterative time-to-go estimation algorithms for the above mentioned guidance laws, perform piecewise-iterative prediction to the future velocity of anti-ship missiles for two flight cases: one for turning flight on level, the other for nearly straight flight on level, and then make corrections to the current time-to-go estimation algorithms. A range-to-go estimation formula is also given for the biased proportional navigation guidance law with impact angle control in the case of nearly straight flight on level. Numerical simulations are provided to illustrate the effectiveness of the proposed algorithm.

Key words: proportional navigation guidance, biased proportional navigation guidance, time-to-go estimation, lead angle, impact time control, anti-ship missiles, time varying velocity, velocity prediction

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