A Composite Sliding Mode Control Scheme Based on Reaction Jets and Flaps for Near-Space Hypersonic Vehicles

doi:10.12382/bgxb.2021.0690

Abstract

Abstract:

To address the underactuation and strong coupling of lifting-body hypersonic reentry vehicle, a composite sliding mode control scheme based on reaction jets and flaps is proposed. Due to the thermal protection requirements, instead of traditional rudders, two body flaps are mounted at the aft windward side of the vehicle to control pitch, yaw and roll channels. The continuous high-frequency and wide-margin vibration of the sideslip angle caused by strong aerodynamic coupling will cause aileron to saturate for a long time, leading to an instable control system. To alleviate the vibration of the sideslip angle and realize quick convergence, an integrated control system is built by employing a pair of reaction jets that can be turned on or off as auxiliary actuators in the yaw channel. Then, based on the linear quadratic optimal control and sliding mode control theory, the control laws for flaps and reaction jets are designed. Simulations using the new composite control scheme and a conventional flap-based control scheme are compared under two command tracking conditions. The results show that the composite control system can effectively suppress the chattering phenomenon of the yaw channel, leading to a rapid convergence of the sideslip angle. Moreover, the novel scheme also improves the stability and speed of tracking in pitch and roll channels.

Key words: hypersonic vehicle, composite control scheme, flap, reaction jet, sliding mode control

CLC Number:

V448.133

DONG Jinlu, MA Yuemeng, ZHOU Di, GONG Xiaogang, ZHANG Xi, SONG Jiahong. A Composite Sliding Mode Control Scheme Based on Reaction Jets and Flaps for Near-Space Hypersonic Vehicles[J]. Acta Armamentarii, 2023, 44(2): 496-506.

Figures/Tables 16

Fig.1 Schematic diagram of a hypersonic vehicle with the composite control scheme

Table 1 Aerodynamic parameters in the pitch channel

a₁	a₂	a₃	a₄	a₅	a₆
0.0634	-13.0238	59.093	0.0952	0.0026	0.9

Table 2 Parameters in the roll and yaw channels

b₁	b₂	b₄	b₆	b₇	k₁	l_y
0.063	313.45	0.092	-0.9	-1.555	4.141	0.006

Table 3 Parameters in the roll and yaw channels

c₁	c₂	c₃	c₄
0.063	-272.139	7.775	0

Fig.2 Response curve of the angle of attack (Case 1)

Fig.3 Response curve of the sideslip angle (Case 1)

Fig.4 Response curve of the roll angle (Case 1)

Fig.5 Response curve of the aileron (Case 1)

Fig.6 Response curve of the elevator (Case 1)

Fig.7 Response curve of lateral jets (Case 1)

Fig.8 Response curve of the angle of attack (Case 2)

Fig.9 Response curve of the roll angle (Case 2)

Fig.10 Response curve of the sideslip angle (Case 2)

Fig.11 Response curve of aileron (Case 2)

Fig.12 Response curve of elevator (Case 2)

Fig.13 Response curve of lateral jets (Case 2)

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