宇航学报

宇航学报 ›› 2017, Vol. 38 ›› Issue (3): 296-303.doi: 10.3873/j.issn.1000-1328.2017.03.010

• 制导、导航、控制与电子 • 上一篇    下一篇

固定时间收敛的再入飞行器全局滑模跟踪制导律

王伯平，王亮，盛永智   

  1. 1. 空军航空大学航空理论系，长春130022；2. 北京理工大学自动化学院，北京100081
  • 收稿日期:2016-09-28 修回日期:2016-12-13 出版日期:2017-03-15 发布日期:2017-03-25
  • 基金资助:

    国家自然科学基金（11402020）

A Global Sliding Mode Based Tracking Guidance Law with Fixed Time Convergence for Reentry Vehicle

WANG Bo ping, WANG Liang, SHENG Yong zhi   

  1. 1. Department of Aviation Theory Aviation University of Air Force, Changchun 130022, China; 2. School of Automation, Beijing Institute of Technology, Beijing 100081, China
  • Received:2016-09-28 Revised:2016-12-13 Online:2017-03-15 Published:2017-03-25

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摘要：

针对再入飞行器模型强非线性、强耦合、快时变和不确定性的特点，以及再入飞行过程中复杂多变的飞行环境，本文提出了一种具有强鲁棒性的全局滑模跟踪制导律设计方法。首先，给出存在干扰的无动力飞行三自由度再入制导模型，以采用经度作为标准参考轨迹的插值因变量为例，将三变量的轨迹跟踪任务转化为对高度和纬度的二个变量的跟踪；然后提出了一种固定时间收敛的全局滑模跟踪制导律，可实现对参考轨迹的鲁棒跟踪，且可保证轨迹跟踪误差在设定的时刻收敛；最后通过对再入飞行器的仿真研究，验证所设计轨迹跟踪制导算法的有效性。

关键词: 再入飞行器, 轨迹跟踪, 全局滑模, 固定时间收敛

Abstract:

The model of reentry vehicle is strongly coupling, nonlinear, fast time-varying and uncertain. And its flight environment is complex and highly variable. To eliminate these bad effects in the design of control and guidance, a global sliding mode based tracking guidance law with fixed-time convergence is investigated in this paper. Firstly, the three-degree-of-freedom reentry guidance model is proposed. And we take the longitude as the dependent variable of the interpolation instead of the time in the standard reference trajectory. So the trajectory of the three variables is transformed into the tracking of the height and latitude. Then, a global sliding mode based tracking guidance law with fixed-time convergence is designed for the trajectory tracking matters. Finally, some simulations are shown to illustrate the effectiveness of the trajectory-tracking guidance algorithm.

Key words: Reentry vehicle, Trajectory tracking, Global sliding mode, Fixed time convergence

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