Design of coordinated gain scheduled attitude controller for reusable booster vehicle

XU Jiang-tao; CUI Nai-gang; LV Shi-liang

doi:10.3788/OPE.20101812.2590

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Design of coordinated gain scheduled attitude controller for reusable booster vehicle

Article | 更新时间：2020-08-12

- Design of coordinated gain scheduled attitude controller for reusable booster vehicle
- Optics and Precision Engineering Vol. 18, Issue 12, Pages: 2590-2596(2010)
- 作者机构：
  
  1. 中国科学院长春光学精密机械与物理研究所, 吉林长春 130033
  2. 哈尔滨工业大学航天学院航天工程系,黑龙江哈尔滨,150001
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20101812.2590
  CLC： V448.12
- Received：24 December 2009，
  
  Revised：15 April 2010，
  
  Published Online：25 December 2010，
  
  Published：25 December 2010
- 稿件说明：
移动端阅览
许江涛, 崔乃刚, 吕世良. 协调增益调度的重复使用助推器姿态控制设计[J]. 光学精密工程, 2010,18(12): 2590-2596

XU Jiang-tao, CUI Nai-gang, LV Shi-liang. Design of coordinated gain scheduled attitude controller for reusable booster vehicle[J]. Editorial Office of Optics and Precision Engineering, 2010,18(12): 2590-2596
许江涛, 崔乃刚, 吕世良. 协调增益调度的重复使用助推器姿态控制设计[J]. 光学精密工程, 2010,18(12): 2590-2596 DOI： 10.3788/OPE.20101812.2590.

XU Jiang-tao, CUI Nai-gang, LV Shi-liang. Design of coordinated gain scheduled attitude controller for reusable booster vehicle[J]. Editorial Office of Optics and Precision Engineering, 2010,18(12): 2590-2596 DOI： 10.3788/OPE.20101812.2590.

摘要

针对可重复使用助推飞行器在大攻角飞行过程中的耦合及干扰问题

提出了基于协调增益调度策略的姿态控制器设计方法。首先

忽略大攻角飞行时俯仰、偏航、滚转通道间潜在的耦合

建立了有别于小扰动线性化的各通道线性化模型

独立设计了各通道的增益调度控制器。然后

在单通道控制的基础上

说明了协调增益调度控制策略的思想。最后

设计了协调调度控制器用于消除通道间的交叉耦合。非线性实时仿真表明

该策略使攻角最大误差降低了1~2

侧滑角跟踪精度提高了将近0.4

满足可重复使用助推飞行器大攻角飞行时对系统性能指标的要求

同时控制策略的设计方法物理概念清晰

易于工程实现。

Abstract

In consideration of the serious coupling and distributions in the attitude control of a reusable booster with a high angle of attack

a new kind of gain-scheduled attitude control strategy was presented. Firstly

each of the pitch

yaw and roll channels was treated separately by ignoring the intentional coupling among the channels

and the linear control model of each channel was established in a way different from that considering small perturbation linearization. Then

the gain-scheduled controller for each channel was designed

and the theory of coordinated gain scheduled control strategy was put forward based on the single gain-scheduled controller. Finally

the coordinated scheduled controller was designed to deal with the intentional cross coupling among different channels. The results of nonlinear real-time simulation validate that the tracking error of the attack angle has reduced about 2

and the control accuracy of sideslip angle has improved about 0.4 by proposed strategy. The control system can satisfy the control performance requirement of the reusable booster

and the strategy of controller design is characterized by its clear physical concepts and easy engineering applications.

关键词

Keywords

references

CAPLIN J. Descent-phase control of a reusable launch vehicle . Aerospace, EI Segundo, CA, USA IEEE 9. D, 2002:1-11.[2] MEON P P, PREMPAIN E, POSTLETHWAITE I,et al.. An LPV loop shaping controller design for the NASA-HL-20 re-entry vehicle .Guidance. Navigation and Control Conference AIAA, Chicago,2009.[3] PREMPAIN E, POSTLETHWAITE I. L2 and H2 performance analysis and gain scheduling synthesis for parameter dependent systems [J]. Automatic, 2008,8(44):2081-2089.[4] JACOB R, BALAS G J,GARRARD W L. Robust dynamic inversion for control of highly maneuverable aircraft[J].Journal of Guidance, Control And Dynamics, New York AIAA, 1995,1(18):18-24.[5] THEODOULIS S,DUC G. Gain scheduled autopilot synthesis for an atmosphere re-entry vehicle . Guidance, Navigation and Control Conference and Exhibit, AIAA Honolulu, Hawaii:2008-7469.[6] STEIN G, DOYLE J C. Beyond singular values and loop shapes[J]. Journal of Guidance, Dynamic and Control, 1991,1(14):5-16.[7] KENJI F, SHINJI I. Research activities to realize advanced space transportation system . AIAA Dayton, Ohio :2008-2575.[8] COSTA R R. Re-entry flight controller design using nonlinear dynamic inversion . Guidance, Navigation and Control Conference and Exhibit. AIAA, Montreal, Canada, 2001:4219-4230.[9] NORIHIO K, KAKASHI K, JUNICHIRO K. Nonlinear dynamical analysis for a reentry vehicle[J]. Trans. Japan Soc. Aero. Space Sci. 2004,156(47):99-107.[10] SCHUMACHER C, KHARGONEKAR P P. Missile autopilot design using control with gain scheduling and dynamic inversion[J]. Journal of Guidance, Control, and Dynamics, Michigan, 1998,2(21):234-243.

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