北京航空航天大学学报 ›› 2021, Vol. 47 ›› Issue (2): 197-206.doi: 10.13700/j.bh.1001-5965.2020.0264

• 论文 • 上一篇    下一篇

一种基于模糊控制的平稳滑翔再入制导律

周锐1,2, 张宇航3, 熊伟4, 史智广5   

  1. 1. 北京航空航天大学 自动化科学与电气工程学院, 北京 100083;
    2. 中国电子科技集团公司航天信息应用技术重点实验室, 石家庄 050081;
    3. 北京航天长征飞行器研究所, 北京 100076;
    4. 北京宇航系统工程研究所, 北京 100076;
    5. 北京临近空间飞艇技术开发有限公司, 北京 100070
  • 收稿日期:2020-06-15 发布日期:2021-03-08
  • 通讯作者: 张宇航 E-mail:zhyhbuaa@163.com
  • 作者简介:周锐,男,博士,教授,博士生导师。主要研究方向:飞行器自主控制、多飞行器协同控制;张宇航,男,硕士,助理工程师。主要研究方向:再入飞行器设计;熊伟,男,硕士,高级工程师。主要研究方向:轨道设计与研究;史智广,男,硕士,研究员。主要研究方向:临近空间飞行器总体技术。
  • 基金资助:
    国家自然科学基金(61773031);中国电子科技集团公司航天信息应用技术重点实验室开放基金

A reentry steady glide guidance algorithm based on fuzzy control

ZHOU Rui1,2, ZHANG Yuhang3, XIONG Wei4, SHI Zhiguang5   

  1. 1. School of Automation Science and Electrical Engineering, Beihang University, Beijing 100083, China;
    2. CETC Key Laboratory of Aerospace Information Application, Shijiazhuang 050081, China;
    3. Beijing Aerospace Long March Vehicle Research Institute, Beijing 100076, China;
    4. China Academy of Launch Vehicle Technology Systems Engineering Division, Beijing 100076, China;
    5. Beijing Near Space Airship Technology Development Co., Ltd., Beijing 100070, China
  • Received:2020-06-15 Published:2021-03-08

摘要: 针对升力式高超声速飞行器(LHV)再入滑翔过程中的周期性振荡现象,提出了一种基于模糊推理与控制的反馈调节方法以抑制振荡实现平稳滑翔。纵向制导在落点误差预测及指令校正的基础上,在倾侧角外环控制回路增加以高度变化率及空速作为输入的模糊控制器对倾侧角指令进行调节,横侧向制导通过航向角误差走廊约束及倾侧角反转逻辑实现大横程条件下的侧向控制。所提方法不依赖于准平衡滑翔条件(QEGC),同时避免了参数化反馈控制律中的反馈项参数设计问题,具有较强的自适应能力。LHV制导实例仿真表明,所提方法可有效抑制振荡现象,满足终端约束及再入走廊约束,方法的鲁棒性也通过Monte Carlo仿真得到了验证。

关键词: 升力式高超声速飞行器(LHV), 平稳滑翔, 预测校正, 模糊控制器, 再入走廊

Abstract: Considering the periodic oscillation in reentry glide of Lifting Hypersonic Vehicle (LHV), a feedback correction method based on fuzzy logic and fuzzy control is proposed to reduce the oscillation and keep reentry glide trajectory smooth. First, the longitudinal guidance is developed based on the prediction of the landing error and the correction of the guidance command, and a fuzzy controller whose input consists of altitude ratio and airspeed is applied to outer loop of the bank angle control system. Then, the lateral guidance is designed by the course angle error corridor and bank reversal logic, which realizes the lateral controls in large transverse range conditions. This method is independent of Quasi-Equilibrium Glide Condition (QEGC) and the problem of parameters design in parametric feedback law is avoided, which enhances the adaptive ability. Based on LHV model, the numerical simulations show that periodic oscillation is effectively reduced by the fuzzy feedback control law within terminal and reentry corridor constraints. Meanwhile, the Monte Carlo simulation with random dispersions and errors verifies the robustness of the proposed algorithm.

Key words: Lifting Hypersonic Vehicle (LHV), steady glide, predictor-corrector, fuzzy controller, reentry corridor

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