Sliding-mode control for a rolling-missile with input constraints

doi:10.23919/JSEE.2020.000078

Journal of Systems Engineering and Electronics ›› 2020, Vol. 31 ›› Issue (5): 1041-1050.doi: 10.23919/JSEE.2020.000078

• Control Theory and Application • Previous Articles Next Articles

Sliding-mode control for a rolling-missile with input constraints

Siyu HUA^1,*(), Xugang WANG^2,*(), Yin ZHU²()

¹ The 802 Institute of Shanghai Academy of Space Flight Technology, Shanghai 201100, China
² School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, China

Received:2019-06-05 Online:2020-10-30 Published:2020-10-30
Contact: Siyu HUA,Xugang WANG E-mail:Rain_HSY@163.com;wxgnets@163.com;zynets@163.com
About author:HUA Siyu was born in 1992. She received her M.S. degree in ordnance launch theory and technology from Nanjing University of Science and Technology, Nanjing, China, in 2018. From 2018 to 2019, she was an engineer in the 802 Institute of Shanghai Academy of Space Flight Technology. Her research interests include flight aerodynamics, guidance and control. E-mail: Rain_HSY@163.com|WANG Xugang was born in 1979. He received his Ph.D. degree in navigation, guidance and control from Northwestern Polytechnical University, Xi'an, China, in 2009. He is a research fellow in School of Energy and Power Engineering, Nanjing University of Science and Technology. His research interests include navigation, guidance and control. E-mail: wxgnets@163.com|ZHU Yin was born in 1995. He received his M.S. degree in ordnance launch theory and technology from Nanjing University of Science and Technology, Nanjing, China, in 2020. His research interests include flight aerodynamics and control. E-mail: zynets@163.com
Supported by:
the Fundamental Research Funds for the Central Universities(30919011401);This work was supported by the Fundamental Research Funds for the Central Universities (30919011401)

Abstract

Abstract:

This paper investigates the overload stabilization problem of the rolling-missile subject to parameters uncertainty and actuator saturation. In order to solve this problem, a sliding-mode control (SMC) scheme is technically employed by using the backstepping approach to make the dynamic system stable. In addition, SMC with the tanh-type switching function plays an important role in reducing intrinsic vibration. Furthermore, an auxiliary system (AS) is developed to compensate for nonlinear terms arising from input saturation. Finally, the simulation results provide a solution to demonstrate that the suggested SMC and the AS methodology have advantages of strong tracking capability, anti-interference ability and anti-saturation performance.

Key words: input constraint, back-stepping approach, slidingmode control (SMC), auxiliary control system

Siyu HUA, Xugang WANG, Yin ZHU. Sliding-mode control for a rolling-missile with input constraints[J]. Journal of Systems Engineering and Electronics, 2020, 31(5): 1041-1050.

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Symbol	Definition
$v$	Flight velocity
$\delta _{y}$, $\delta _{z}$	Elevator angle, rudder angle
$n_{y}$, $n_{z}$	Longitudinal overload, lateral overload
$\omega _{y}$, $\omega _{z}$	Pitch angular rate, yaw rate
$a_{22}$, $a_{24}$, $a_{25}$, $a_{34}$, $a_{35}$	Aerodynamic coefficients
"$-$", "$\Delta $"	Nominal value of the parameter, perturbation value of the parameter
${{{\mathit{\boldsymbol{D}}}}}_{1}, {{{\mathit{\boldsymbol{D}}}}}_{2}$	Uncertainty

Coefficient	$a_{22}$/s$^{ - 1}$	$a_{24}$/s$^{ - 2}$	$a_{25}$/s$^{ - 2}$	$a_{34}$/s$^{ - 1}$	$a_{35}$/s$^{ - 1}$	$a'_{27}$/s$^{ - 2}$	$a'_{28}$/s$^{ - 1}$
Value	-1.164	-88.22	27.479	0.198 1	0.027 4	-8.823	0.068 1

Longitudinal overload $n_{y}$	Lateral overload $n_{z}$	Pitch angular rate $w_{y}$	Yaw rate $w_{z}$
0.02	0.03	1.2	0.5

Control scheme	Rise time $t_{r}$/s	Peak time $t_{p}$/s	Setting time $t_{s}$/s	Overshot $\sigma $/%	Static error
SMC	0.11	0.15	0.09	3	0.02
SMC+30%	0.11	0.15	0.09	4	0.02
SMC+AS	0.15	0.35	0.18	1	0.01

Control scheme	Rise time $t_{r}$/s	Peak time $t_{p}$/s	Setting time $t_{s}$/s	Overshot $\sigma $/%	Static error
SMC	0.11	0.17	0.10	10	0.02
SMC+30%	0.11	0.17	0.10	4	0.03
SMC+AS	0.12	0.17	0.11	1	0.01

Sliding-mode control for a rolling-missile with input constraints

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