北京航空航天大学学报 ›› 2015, Vol. 41 ›› Issue (5): 864-870.doi: 10.13700/j.bh.1001-5965.2014.0488

• 论文 • 上一篇    下一篇

考虑禁飞区规避的预测校正再入制导方法

赵江1, 周锐1, 张超2   

  1. 1. 北京航空航天大学 自动化科学与电气工程学院, 北京 100191;
    2. 试验物理与计算数学国家级重点实验室, 北京 100076
  • 收稿日期:2014-08-01 修回日期:2014-09-26 出版日期:2015-05-20 发布日期:2015-06-02
  • 通讯作者: 周锐(1968—),男,湖北钟祥人,教授,zhr@buaa.edu.cn,主要研究方向为飞行器自主控制、多飞行器协同控制. E-mail:zhr@buaa.edu.cn
  • 作者简介:赵江(1986—),男,陕西西安人,博士研究生,jzhao@buaa.edu.cn
  • 基金资助:

    国家自然科学基金(61273349,61175109,61203223,61333004);航空科学基金(2013ZA18001);北航博士研究生创新基金(YWF-14-YJSY-013)

Predictor-corrector reentry guidance satisfying no-fly zone constraints

ZHAO Jiang1, ZHOU Rui1, ZHANG Chao2   

  1. 1. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
    2. National Key Laboratory of Experimental Physics and Computational Mathematics, Beijing 100076, China
  • Received:2014-08-01 Revised:2014-09-26 Online:2015-05-20 Published:2015-06-02

摘要:

针对升力式高超声速飞行器再入滑翔侧向制导问题,提出了一种考虑禁飞区规避的预测校正制导方法.纵向制导采用落点误差预测与指令校正相结合的方式,不断更新倾侧角的幅值,实时修正轨迹纵程.侧向制导设计了一种倾侧角反转逻辑的切换机制,利用航向角误差走廊和航向角导向区域控制飞行器的侧向运动.CAV-H再入滑翔飞行器制导仿真实例表明,该方法不依赖于标准再入轨迹,能够导引飞行器规避禁飞区约束.Monte Carlo仿真验证表明,在随机初始扰动和误差存在的情况下,该制导方法具有良好的鲁棒性.

关键词: 高超声速飞行器, 再入制导, 预测校正, 禁飞区, 倾侧角反转

Abstract:

To enforce the lateral maneuverability of the reentry gliding flight, a predictor-corrector guidance method satisfying the no-fly zone constraints was proposed for the lifting hypersonic reentry vehicles. First, the longitudinal guidance was developed by the prediction of the landing error and the correction of the guidance command. The downrange was modified in real time by updating the magnitude of the bank angle. Then, a new handoff mechanism for the bank angle reversal logic was designed for the lateral guidance. The maneuver of the lateral motion was performed by employing the heading angle error corridor and the heading angle orienting area. Based on the CAV-H model, the numerical simulations show that the no-fly zone constraints can be satisfied by the predictor-corrector guidance method which is independent of the standard reentry trajectory. The Monte Carlo simulation results of the reentry gliding guidance with random initial dispersions and errors also demonstrate the robustness of the proposed algorithm.

Key words: hypersonic vehicles, reentry guidance, predictor-corrector, no-fly zone, bank angle reversal

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