Control of Quick Turning of Missile with Lateral Thrust and Aerodynamics Based on Neural Network

doi:10.12382/bgxb.2023.0901

Abstract

Abstract:

The control of the quick turning of air-to-air missile is to complete the entire maneuvering process in the shortest possible time under the premise of ensuring the stable flight of the missile. In order to achieve the above tactical indicators, a lateral thrust/aerodynamics composite controller based on sliding mode variable structure control and fuzzy logic is designed considering the fast time denaturation, strong nonlinearity and large interference of the missile quick turning. In view of the uncertain initial value and excessive external interference that may occur in actual flight, the fixed-time convergence theory and the extended state observer are introduced to effectively avoid the control input jitter caused by interference and ensure that the attitude angle of missile can converge quickly and stably within a fixed time. The neural network is used to optimize the design parameters of sliding mode variable structure control, which not only ensures the quick turning of missile, but also reduces the mass of missile's lateral engine. The effectiveness of the proposed control and distribution scheme is verified by simulation. The designed controller has certain robustness, stable and smooth control effect, strong anti-interference ability and excellent attitude tracking performance in complex situations such as model uncertainty and external interference, and the tracking effect of the control algorithm after parameter optimization is better, which reduces the original convergence time by 12.6% and the original maximum control force by 9.6%.

Key words: quick turning, composite control, sliding mode variable structure control, extended state observer, fuzzy control, neural networks

CLC Number:

V249
TJ765.2

PEI Xinyue, YU Yong, LI Zheng, LI Jiaxun, YU Jianqiao. Control of Quick Turning of Missile with Lateral Thrust and Aerodynamics Based on Neural Network[J]. Acta Armamentarii, 2024, 45(10): 3564-3576.

Figures/Tables 15

Fig.1 Schematic diagram of the layout of missile with lateral thrust and aerodynamics

Fig.2 Schematic diagram of fuzzy control principle

Table 1 Rudder command assignment fuzzy rules

\|α\|	\|e₁\|
\|α\|	ZO	PS	PM	PB
ZO	ZO	PM	PB	PB
PS	ZO	PM	PM	PB
PM	ZO	PS	PM	PM
PB	ZO	ZO	PS	PS

Table 2 Controller parameters

参数	数值	参数	数值
m₁	1.5	α₁	0.5
m₂	0.8	β₁	4.0
k₁	3.0	n₁	1.5
k₂	1.5	n₂	0.5

Table 3 ESO parameters

参数	数值	参数	数值
ε	0.1	σ₁	1.0
δ_E	0.2	σ₂	1.0
a	0.8

Fig.3 Quick turning trajectory of missile

Fig.4 Ballistic inclination, pitch angle, angle of attack

Fig.5 Pitch angular velocity

Fig.6 Speed

Fig.7 Overload

Fig.8 Direct force valve opening

Fig.9 Comparison of tracking performances under aerodynamic pull offset and no aerodynamic pull offset

Fig.10 Comparison of fuzzy and ref.[24] assignment methods outputs

Table 4 Optimized controller parameters

参数	优化后数值	优化前数值
m₁	1.01	1.5
m₂	0.99	0.8
k₁	4.64	3.0
k₂	3.5	1.5
α₁	0.01	0.5
β₁	4.12	4.0
n₁	1.01	1.5
n₂	0.18	0.5

Fig.11 Tracking performances and outputs before and after optimization

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