Decoupling Control Method Based on Incremental Nonlinear Dynamic Inversion for Missiles

CHEN Xingyang; ZHAO Xia; ZHOU Xiaozhi; LI Liang

doi:10.15892/j.cnki.djzdxb.2024.02.012

Journal of Projectiles, Rockets, Missiles and Guidance >

2024 , Vol. 44 >Issue 2: 76 - 81

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2024.02.012

Decoupling Control Method Based on Incremental Nonlinear Dynamic Inversion for Missiles

CHEN Xingyang ¹^,² ,
ZHAO Xia ¹ ,
ZHOU Xiaozhi ¹^,² ,
LI Liang ¹

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¹ China Airborne Missile Academy, Luoyang 471009, Henan, China
² National Key Laboratory of Air-based Information Perception and Fusion, Luoyang 471009, Henan, China

Received date: 2023-09-25

Online published: 2024-12-28

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Abstract

To deal with the strong coupling dynamics existed in high angle of attack maneuvers, an incremental nonlinear dynamic inversion(INDI) control is proposed in this paper. The flight control system for missiles is divided into fast angular velocity loop with high bandwidth and slow angular loop with low bandwidth, then the incremental dynamic inversion control law is proposed to cancel its coupling dynamics for each loop, respectively. Thus, the decoupling control is achieved. Simulation of typical working condition shows that the proposed incremental nonlinear inversion decoupling control law can greatly improve the stability control performance with strong coupling dynamics. Compared to traditional PID control, the INDI control can completely eliminate low-frequency oscillation and overshoot of overload response. At the same time, it also enables the roll angle response to accurately track command.

Key words： autopilot; coupling; incremental nonlinear dynamic inversion; decoupling control

Cite this article

CHEN Xingyang , ZHAO Xia , ZHOU Xiaozhi , LI Liang . Decoupling Control Method Based on Incremental Nonlinear Dynamic Inversion for Missiles[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2024 , 44(2) : 76 -81 . DOI: 10.15892/j.cnki.djzdxb.2024.02.012

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References

Publishing order | Descend order by publishing year | Descend order by cited within

[1]	孙超逸, 刘全军, 王颖, 等. 高速飞行器横侧向耦合振荡发散机理及控制策略研究题[J]. 导弹与航天运载技术, 2022, 388(4): 35-38. SUN C Y, LIU Q J, WANG Y, et al. Research on lateral coupling oscillation divergence mechanism and control strategy of high-speed aircraft[J]. Missiles and Space Vehicles, 2022, 388(4): 35-38.

[2]	姚德清, 魏毅寅, 杨志红, 等. 空天飞行器制导控制技术研究进展与展望[J]. 宇航学报, 2020, 41(7): 850-859. YAO D Q, WEI Y Y, YANG Z H, et al. Progress and prospect of research on guidance and control technology of aerospace vehicle[J]. Journal of Astronautics, 2020, 41(7): 850-859.

[3]	周军, 周凤岐, 李言俊. 飞行器耦合通道控制系统的独立设计方法研究[J]. 宇航学报, 1998(4): 66-70. ZHOU J, ZHOU F Q, LI Y J. Aircraft coupling channel control system independent design study[J]. Journal of Astronautics. 1998(4): 66-70.

[4]	李帆, 周凤岐. 大迎角下导弹气动耦合控制系统分析[J]. 飞行力学, 2001, 19(1): 63-66. LI F, ZHOU F Q. Analyses on the missile's aerodynamic coupling control system with large angle of attack[J]. Flight Dynamics, 2001, 19(1): 63-66.

[5]	LIN C F, CLOUTIER J R, EVERS J H. High-performance robust bank-to-turn missile autopilot design[J]. Journal of Guidance, Control and Dynamics, 1995, 18(1): 46-54.

[6]	LAVRETSKY E, WISE K A. Robust and adaptive control: with aerospace applications[M]. Berlin: 2013.

[7]	SONNEVELDT L. Adaptive backstepping flight control for modern fighter aircraft[D]. Delft: Delft University of Technology, 2010.

[8]	童春霞, 王正杰, 张天桥. BTT导弹的变结构解耦控制系统设计[J]. 宇航学报, 2006, 27(1): 27-30. TONG C X, WANG Z J, ZHANG T Q. Decoupling system design based on variable structure system for BTT missile[J]. Journal of Astronautics, 2006, 27(1): 27-30.

[9]	罗杰·W·普拉特. 飞行控制系统设计和实现中的问题[M]. 陈宗基, 张平, 译. 上海: 上海交通大学出版社, 2015. PRATT R W. Flight control systems practical issues in design and implementation[M]. CHEN Z J, ZHANG P, translate. Shanghai: Shanghai Jiao Tong University Press, 2015.

[10]	雷延花, 陈士橹. 导弹气动耦合分析与解耦算法研究[J]. 弹道学报, 2003, 15(1): 11-16. LEI Y H, CHEN S L. The missile aerodynamic coupling analysis and decoupling arithmetic study[J]. Journal of Ballistics, 2003, 15(1): 11-16.

[11]	SIEBERLING S, CHU Q P, MULDER J A. Robust flight control using incremental nonlinear dynamic inversion and angular acceleration prediction[J]. Journal of Guidance, Control, and Dynamics, 2010, 33(6): 1732-1742.

[12]	SMEUR E J, CHU Q, CROON G C. Adaptive incremental nonlinear dynamic inversion for attitude control of micro air vehicles[J]. Journal of Guidance, Control, and Dynamics, 2016, 39(3): 450-461.

[13]	常怡鹏, 王小平, 林秦颖, 等. 基于神经网络补偿动态逆误差的导弹控制器设计[J]. 弹箭与制导学报, 2020, 40(1): 150-154. CHANG Y P, WANG X P, LIN Q Y, et al. Missile controller design based on neural network compensating dynamic inverse error[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2020, 40(1): 150-154.

[14]	陈阳, 马建伟. 基于非线性干扰观测器的旋转导弹动态逆控制器设计[J]. 火力与指挥控制, 2018, 43(8): 156-159. CHEN Y, MA J W. Dynamic inversion control for spinning missile based on nonlinear disturbance observer[J]. Fire Control and Command Control, 2018, 43(8): 156-159.

[15]	张友安, 杨华东, 顾文锦. 空空导弹控制系统鲁棒动态逆设计[J]. 系统工程与电子技术, 2004, 26(8): 1084-1089. ZHANG Y A, YANG H D, GU W J. Robust dynamic inversion controller design for air-to-air missiles[J]. Systems Engineering and Electronic, 2004, 26(8): 1084-1089.

[16]	BUGAJSKI J D, ENNS D F. Nonlinear control law with application to high angle of attack flight[J]. Journal of Guidance, Control and Dynamics, 1992, 15(3): 761-767.

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