吸气式高超声速飞行器纵向运动反演控制器设计

时建明; 王洁; 王琨; 邵雷

doi:10.7652/xjtuxb201303019

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吸气式高超声速飞行器纵向运动反演控制器设计

更新时间：2025-07-09

- 吸气式高超声速飞行器纵向运动反演控制器设计
- Design of Backstepping Controller for Longitudinal Motion of an Air-Breathing Hypersonic Vehicle
- 西安交通大学学报 2013年47卷第3期页码：102-107
- 作者机构：
  
  空军工程大学防空反导学院,西安,710051
- 作者简介：
- 基金信息：
  
  : 2012-06-11。作者简介: 时建明(1984—),男,博士生;王洁(通信作者),女,教授,博士生导师。基金项目: 航空科学基金资助项目(20120196006, 20110196005)
- DOI：10.7652/xjtuxb201303019
  中图分类号： V448;TP273
- 网络首发：2013-03-10，
  
  纸质出版：2013
- 稿件说明：
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时建明, 王洁, 王琨, 等. 吸气式高超声速飞行器纵向运动反演控制器设计[J]. 西安交通大学学报, 2013,47(3):102-107.

Design of Backstepping Controller for Longitudinal Motion of an Air-Breathing Hypersonic Vehicle[J]. 2013, 47(3): 102-107.
时建明, 王洁, 王琨, 等. 吸气式高超声速飞行器纵向运动反演控制器设计[J]. 西安交通大学学报, 2013,47(3):102-107. DOI： 10.7652/xjtuxb201303019.

Design of Backstepping Controller for Longitudinal Motion of an Air-Breathing Hypersonic Vehicle[J]. 2013, 47(3): 102-107. DOI： 10.7652/xjtuxb201303019.

摘要

针对气动/推进/结构耦合的吸气式高超声速飞行器纵向平面飞行控制问题

提出了基于反演的鲁棒控制器设计方法。利用曲线拟合模型将控制系统表示为反馈形式

采用反演方法设计虚拟和实际控制器

并引入鲁棒微分器估计虚拟控制量的导数

解决了虚拟控制量求导运算复杂的问题。为增强控制器应对不确定项的鲁棒性

设计了超扭曲滑模干扰观测器

实现了对系统模型不确定项的估计和补偿。对吸气式高超声速飞行器一体化原理模型的速度和高度指令跟踪仿真表明

该控制器对拟合误差和外加干扰等系统不确定项具有鲁棒性

系统状态量能够在指令跟踪过程中趋于平衡状态

从而验证了所提方案的有效性。

Abstract

A robust controller based on backstepping design procedure is proposed for an air-breathing hypersonic vehicle with aerodynamic

propulsion and structural couplings. Expressing the control system as strict feedback form via the curve-fitted model

virtual and actual controllers are constructed for the velocity and altitude subsystems. To omit analytic calculation of the virtual control law derivatives

which is very difficult to evaluate in the traditional backstepping control

robust differentiators are introduced. Super-twisting sliding mode disturbance observers are designed to compensate uncertainties in the system dynamics. Trajectory tracking simulation performed on the first principle model of the vehicle's longitudinal dynamics shows that the designed controllers are robust to model fitting errors and outside disturbances

and the system states reach trimmed condition asymptotically.

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Keywords

references

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HANK J M, MURPHY J S, MUTZMAN R C. The X-51A scramjet engine flight demonstration program [C]∥Proceedings of 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, VA, USA: AIAA, 2008: 1-13.

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XU Haojian, MIRMIRANI M D, IOANNOU P A. Adaptive sliding mode control design for a hypersonic flight vehicle [J]. Journal of Guidance, Control, and Dynamics, 2004, 27(5): 829-838.

高道祥, 孙增圻, 罗熊, 等. 基于Backstepping的高超声速飞行器模糊自适应控制 [J]. 控制理论与应用, 2008, 10, 25(5): 805-810.

GAO Daoxiang, SUN Zengqi, LUO Xiong, et al. Fuzzy adaptive control for hypersonic vehicle via backstepping method [J]. Control Theory Applications, 2008, 10, 25(5): 805-810.

XU Bin, GAO Daoxiang, WANG Shixing. Adaptive neural control based on HGO for hypersonic flight vehicles [J]. Science China: Information Science, 2011, 54(3): 511-520.

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