Robust missile autopilot design based on dynamic surface control

doi:10.23919/JSEE.2022.000154

Journal of Systems Engineering and Electronics ›› 2023, Vol. 34 ›› Issue (1): 160-171.doi: 10.23919/JSEE.2022.000154

• CONTROL THEORY AND APPLICATION • Previous Articles Next Articles

Robust missile autopilot design based on dynamic surface control

Jianping ZHOU(), Wei LI(), Qunli XIA(), Huan JIANG()

¹ School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received:2021-02-05 Online:2023-02-18 Published:2023-03-03
Contact: Qunli XIA E-mail:6043105@qq.com;cooper1994@126.com;1010@bit.edu.cn;h.jiang@bit.edu.cn
About author:
ZHOU Jianping was born in 1977. He received his B.E. degree from Chongqing University in 2000, and M.E. degree from University of Electronic Science and Technology of China in 2008. Now he is a Ph.D. candidate in Beijing Institute of Technology. His research interest is missile guidance and control. E-mail: 6043105@qq.com

LI Wei was born in 1994. He received his B.E. and M.E. degrees from Beijing Institute of Technology in 2015, and 2018 respectively. Now he is a Ph.D. candidate in Beijing Institute of Technology. His research interests are missile guidance and control, cooperative guidance and control of multiple flight vehicles. E-mail: cooper1994@126.com

XIA Qunli was born in 1971. He received his B.E. degree in launching engineering, M.E. degree in flight mechanics and Ph.D. degree in aircraft design from Beijing Institute of Technology in 1993, 1996, and 1999 respectively. He is currently an associate professor in Beijing Institute of Technology. His research interest is missile guidance and control technology. E-mail: 1010@bit.edu.cn

JIANG Huan was born in 1994. He received his B.E. degree from Shenyang Aerospace University in 2015, and he studied for his M.E. degree in Beijing Institute of Technology from 2015. Now he is a Ph.D. candidate in Beijing Institute of Technology from 2017. His research interests include aerospace system dynamics, flight guidance control and computational optimization for trajecotry planning. E-mail: h.jiang@bit.edu.cn
Supported by:
This work was supported by Joint Fund of the Ministry of Education for Equipment Pre-research (6141A20223)

Abstract

Abstract:

Since the dynamical system and control system of the missile are typically nonlinear, an effective acceleration tracking autopilot is designed using the dynamic surface control (DSC) technique in order to make the missile control system more robust despite the uncertainty of the dynamical parameters and the presence of disturbances. Firstly, the nonlinear mathematical model of the tail-controlled missile is decomposed into slow acceleration dynamics and fast pitch rate dynamics based on the naturally existing time scale separation. Secondly, the controller based on DSC is designed after obtaining the linear dynamics characteristics of the slow and fast subsystems. An extended state observer is used to detect the uncertainty of the system state variables and aerodynamic parameters to achieve the compensation of the control law. The closed-loop stability of the controller is derived and rigorously analyzed. Finally, the effectiveness and robustness of the design is verified by Monte Carlo simulation considering different initial conditions and parameter uptake. Simulation results illustrate that the missile autopilot based DSC controller achieves better performance and robustness than the other two well-known autopilots. The method proposed in this paper is applied to the design of a missile autopilot, and the results show that the acceleration tracking autopilot based on the DSC controller can ensure accurate tracking of the required commands and has better performance.

Key words: acceleration autopilot, nonlinear missile dynamics, time-scale separation, extended state observer, dynamic surface control (DSC)

Jianping ZHOU, Wei LI, Qunli XIA, Huan JIANG. Robust missile autopilot design based on dynamic surface control[J]. Journal of Systems Engineering and Electronics, 2023, 34(1): 160-171.

Figures/Tables 10

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Variable	Value
$ m $ /kg	204.01
$ S $ /m²	0.040877
$ L $ /m	0.2286
$ {I_y} $ /(kg·m²)	247.42
$ {c_a} $	−0.3
$ {w_s} $ /(rad/s)	150
$ {\mu _s} $	0.7
$ {a_n} $ /(°)⁻³	0.000103
$ {a_m} $ /(°)⁻³	0.000215
$ {b_n} $ /(°)⁻²	−0.00945
$ {b_m} $ /(°)⁻²	−0.0195
$ {c_n} $ /(°)⁻¹	−0.1696
$ {c_m} $ /(°)⁻¹	0.051
$ {d_n} $ /(°)⁻¹	−0.034
$ {d_m} $ /(°)⁻¹	−0.206

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Robust missile autopilot design based on dynamic surface control

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