临近空间高超声速飞行器的直接力与襟翼复合滑模控制

doi:10.12382/bgxb.2021.0690

摘要/Abstract

摘要：

为解决升力体构型再入高超声速飞行器的欠驱动强耦合问题,提出一种直接力与襟翼的复合滑模控制方案。再入式高超声速飞行器由于热防护要求以两片体襟翼控制俯仰、偏航和滚转3个通道,强气动耦合所引发侧滑角的持续高频大幅抖动将造成副翼控制量长时间处于饱和状态,进而导致控制系统失稳。为抑制侧滑角的抖动并使其快速收敛,在偏航通道引入一对具有开关特性的侧喷发动机,将系统构建为一个复合控制系统,并基于线性二次型最优控制与滑模控制理论分别为襟翼和侧喷发动机设计了控制律。在两种指令跟踪情形下将复合控制与常规襟翼控制方案进行仿真对比。仿真结果表明,新的复合控制系统能有效地抑制偏航通道的抖振现象,且使侧滑角快速收敛,同时能够使攻角与滚转角快速稳定地跟踪制导指令。

关键词: 高超声速飞行器, 复合控制, 襟翼, 侧喷发动机, 滑模控制

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

中图分类号:

V448.133

董金鲁, 马悦萌, 周荻, 龚晓刚, 张曦, 宋加洪. 临近空间高超声速飞行器的直接力与襟翼复合滑模控制[J]. 兵工学报, 2023, 44(2): 496-506.

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.

图/表 16

图1 复合控制高超声速飞行器框架结构图

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

表1 俯仰通道气动参数

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

表2 偏航通道气动参数

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

表3 滚转通道气动参数

Table 3 Parameters in the roll and yaw channels

c₁	c₂	c₃	c₄
0.063	-272.139	7.775	0

图2 攻角响应曲线(情形1)

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

图3 侧滑角响应曲线(情形1)

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

图4 滚转角响应曲线(情形1)

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

图5 副翼响应曲线(情形1)

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

图6 升降舵响应曲线(情形1)

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

图7 直接侧向力响应曲线(情形1)

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

图8 攻角响应曲线(情形2)

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

图9 滚转角响应曲线(情形2)

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

图10 侧滑角响应曲线(情形2)

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

图11 副翼响应曲线(情形2)

Fig.11 Response curve of aileron (Case 2)

图12 升降舵响应曲线(情形2)

Fig.12 Response curve of elevator (Case 2)

图13 直接侧向力响应曲线(情形2)

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

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