北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (9): 1813-1823.doi: 10.13700/j.bh.1001-5965.2016.0751

• 论文 • 上一篇    下一篇

基于虚拟域预测控制的轨迹跟踪方法

樊钰, 闫梁, 朱武宣, 白广周   

  1. 航空工程研究所, 北京 100094
  • 收稿日期:2016-09-20 出版日期:2017-09-20 发布日期:2016-11-16
  • 通讯作者: 闫梁,E-mail:yanliangbj@163.com E-mail:yanliangbj@163.com
  • 作者简介:樊钰,男,硕士研究生;主要研究方向:轨迹跟踪;闫梁,男,博士;主要研究方向:航天任务分析与设计;朱武宣,男,学士,研究员;主要研究方向:飞行器测控总体;白广周,男,学士,研究员;主要研究方向:飞行器测控总体
  • 基金资助:
    国家“863”计划

Trajectory tracking method based on predictive control in virtual domain

FAN Yu, YAN Liang, ZHU Wuxuan, BAI Guangzhou   

  1. Institute of Aerospace Engineering, Beijing 100094, China
  • Received:2016-09-20 Online:2017-09-20 Published:2016-11-16
  • Supported by:
    National High-tech Research and Development Program of China

摘要: 针对在线轨迹实时规划算法,提出了一种基于虚拟域预测控制的轨迹跟踪方法。该方法采用多项式近似系统模型,引入虚拟路径及反动力解算方法,将时域转化为虚拟域,较在时域上近似模型的控制方法解耦效果好,实时性强。通过反动力学解算、非线性规划的输入设置可直接得到连续的控制量,相对于传统非线性预测控制的软约束的方法,从根本上保证了控制量的连续性。以拦截弹道导弹为背景,在初始状态量添加小扰动及末端条件改变的条件下,进行仿真验证。结果表明:与非线性反馈跟踪方法相比,曲线平滑,在遭遇点脱靶量、末端路径倾角及偏角误差较小,实时性同样可满足控制需求。

关键词: 导弹, 控制理论, 标称制导律, 轨迹跟踪, 预测控制, 拦截

Abstract: A trajectory tracking method based on predictive control in the virtual domain is proposed for the algorithm of online real-time trajectory planning. The method uses polynomial approximate system model and introduces virtual path and inverse dynamics to convert time domain into virtual domain. Its advantage is that the decoupling effect is good and it takes less compute time than the control method of approximate model in the time domain. Through inverse dynamics, the import configuration of nonlinear programming ensures the continuous controls, which cannot be guaranteed by the nonlinear predictive control of traditional soft constraint method. In the background of intercepting ballistic missiles, simulation verification is carried out under the condition of initial minor disturbances and terminal condition change. The simulation results demonstrate that, compared with nonlinear feedback tracking method, the curve is smooth, the miss distance, pitch angle error and yaw angle error are small, and instantaneity can meet the control requirements.

Key words: missile, control theory, nominal guidance law, trajectory tracking, predictive control, interception

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