Impact Angle-constrained Dive Maneuver Guidance Method for Hypersonic Vehicles

doi:10.16182/j.issn1004731x.joss.25-0668

Abstract

Abstract:

To address the impact angle control and maneuvering flight problem of hypersonic vehicles in the dive phase, this paper proposed a tracking guidance method integrating optimal Bézier curves and super-twisting sliding mode control. A three-dimensional Bézier curve trajectory satisfying the impact angle constraint was designed, and the maneuvering flight in dive phase was achieved by adding dynamic control points; to optimize impact velocity, a rapid calculation method for the impact velocity of the vehicle flying along the curve was derived, and the optimal reference trajectory was obtained by optimizing the control point parameters through sequential quadratic programming; to ensure precise tracking of the trajectory, a tracking guidance law based on super-twisting sliding mode control was designed. Simulation results demonstrate that this guidance method achieves high control accuracy of impact point and impact angle; under disturbance conditions, it still maintains good robustness and high terminal control precision.

Key words: hypersonic vehicle, dive guidance, impact angle control, Bézier curve, robust tracking

CLC Number:

TP391

Wang He, Lei Gang, Li Shaopeng. Impact Angle-constrained Dive Maneuver Guidance Method for Hypersonic Vehicles[J]. Journal of System Simulation, 2026, 38(6): 1699-1710.

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参数	取值	参数	取值
高度/km	25	航迹角/(°)	0
速度/(m/s)	2 000	航向角/(°)	45
倾侧角/(°)	0	初始点经纬度/(°)	(0, 0)
攻角/(°)	5	目标点经纬度/(°)	(1, 1)

制导方法	落速/(m/s)	落角/(°)	脱靶量/m
参考弹道	1 107.340	-80.000	0
本文方法	1 106.065	-79.892	0.743
文献[11]	925.113	-79.864	1.273

制导方法	落角/(°)	脱靶量/m
本文方法	-79.902	1.086
传统滑模	-79.855	1.567
PID控制	-79.638	5.423

算例	起始点/(°)	期望落角/(°)
I	(0.2, 0)	-70
II	(0.1, 0)	-75
III	(0, 0.1)	-80
IV	(0, 0.2)	-85

算例	x₁/km	x₂/km	实际落角/(°)	脱靶量/m
Ⅰ	81.394	133.219	-69.965	2.473
Ⅱ	87.037	142.838	-74.953	2.024
Ⅲ	84.050	145.146	-79.944	1.513
Ⅳ	72.915	140.187	-84.930	0.637