北京航空航天大学学报 ›› 2013, Vol. 39 ›› Issue (5): 569-573.

• 论文 •    下一篇

高超声速飞行器自适应BTT末制导律

李惠峰, 葛亚杰, 李昭莹   

  1. 北京航空航天大学 宇航学院, 北京 100191
  • 收稿日期:2012-05-10 修回日期:2013-05-07 出版日期:2013-05-31 发布日期:2013-05-22
  • 基金资助:
    国家自然科学基金资助项目(61174221)

Adaptive BTT terminal guidance law for hypervelocity vehicle

Li Huifeng, Ge Yajie, Li Zhaoying   

  1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2012-05-10 Revised:2013-05-07 Online:2013-05-31 Published:2013-05-22

摘要: 针对高超声速飞行器末段打击问题,提出了具有自适应能力的比例导引律,实现了高精度定点定向打击.通过纵向进入条件的分析,设计了一种提高比例导引进入时间的收敛策略,从而使飞行器有足够的时间进行横纵向调整,保证了落角落点约束的满足.由于制导参数直接影响落点和落角的精度,而飞行器动力学约束会导致无法理想响应制导指令,因此设计了一种闭环非线性自适应律,通过在线选择制导参数确保飞行器以高精度命中目标.仿真结果表明了该末制导方法的有效性和准确性.

Abstract: An adaptive proportional navigation guidance law is proposed for hypersonic vehicle terminal guidance. The vehicle could be guided to impact the target precisely in a specific direction with required circular error probable. Based on the analysis of longitudinal flight, a convergence strategy was designed to make the proportional navigation guidance works earlier. The strategy allowed more time for the vehicle to meet the heading constraints at the impact. The precision of impact was affected by guidance parameters directly. However, vehicle would not conduct guidance commands ideally because of dynamic constraints. A close-loop nonlinear adaptive law was introduced to update guidance parameters online to improve the impact precision. Simulation results demonstrate the affectivity and accuracy of the proposed method.

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