Analytical Reentry Guidance Method Based on Lift-to-drag Ratio-velocity Profile

doi:10.16182/j.issn1004731x.joss.25-0855

Abstract

Abstract:

An analytical reentry guidance method based on the lift-to-drag ratio and velocity profile was proposed to address the challenges of precise flight time control and prohibited area avoidance for the hypersonic glide flight vehicle during the reentry phase. A reduced-order reentry motion model was established; the Chebyshev series was used to approximate its nonlinear integral terms and differential equations; analytical expressions for the glide trajectory were yielded. The analytical relationships among flight time, remaining range, and the lift-to-drag ratio and velocity profile were derived. The optimization problem of lift-to-drag ratio and velocity profile was converted into a segmented parameter optimization problem for the angle-of-attack and velocity profile. An online update mechanism was designed to adjust the lift-to-drag ratio profile in real time and combined with the adaptive lateral guidance law based on the improved artificial potential field method, to satisfy both flight time and prohibited area constraints while satisfying conventional reentry constraints. Simulation results demonstrate that the proposed method can effectively coordinate the terminal arrival time sequence of multiple flight vehicles and reliably avoid multiple prohibited areas.

Key words: hypersonic glide flight vehicle, lift-to-drag ratio and velocity profile, analytical reentry guidance, prohibited area constraint, time constraint

CLC Number:

TP448.2

Sun Weibo, Ma Ping, Wang Yuxuan, Wang Songyan, Chao Tao. Analytical Reentry Guidance Method Based on Lift-to-drag Ratio-velocity Profile[J]. Journal of System Simulation, 2026, 38(3): 651-669.

Figures/Tables 28

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Table 1

Terminal state errors in scenarios without no-fly zones

方法	$Δ h f$ /km	$Δ v f$ /(m/s)	$Δ θ f$ /(°)	$Δ t f$ /s	$Δ s t o g o, f$ /km
本文方法	0.21	0	0.05	7.56	-5.8
文献[31]方法	0.27	0	0.03	14.00	-13.5

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Table 8

Initial states of vehicle

飞行器	$h 0$ /km	$v 0$ /(m/s)	$λ 0$ /(°)	$ϕ 0$ /(°)	$ψ 0$ /(°)
1	50	6 500	26.0	20.0	93.0
2	48	6 600	26.5	11.0	85.7
3	48	6 500	27.0	5.7	61.4

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Table 9

Fig. 17

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Table 10

Errors of terminal remaining range and terminal flight time

飞行器	$Δ t f$ /s	$Δ s t o g o, f$ /km
1	8.79	-28.13
2	9.07	-23.31
3	9.21	-24.49

Table 10

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方法	整个制导过程	单制导周期
本文方法	3.76	4.92
文献[31]	19.20	25.30

禁飞区	经度/(°)	纬度/(°)	半径/km	引力衰减半径/km	斥力增强半径/km
1	75	-13	400	430	1 000
2	88	-8	600	730	1 200
3	92	-24	900	1 100	1 500

禁飞区	经度/(°)	纬度/(°)	半径/km	引力衰减半径/km	斥力增强半径/km	速度/(m/s)	航向/(°)
1	13.0	11.0	400	430	1 600	0	0
2	21.0	6.5	400	430	1 500	0	0
3	22.0	18.0	400	430	1 000	12	80
4	30.5	13.2	450	480	1 500	20	60
5	32.0	23.5	500	530	900	0	0

状态类型	高度/km	速度/(m/s)	经度/(°)	纬度/(°)	航迹角/(°)	航向角/(°)
初始	60	6 150	0	0	-0.2	65
终端	25	2 000	—	—	-1.4	—

禁飞区	经度/(°)	纬度/(°)	半径/km	引力衰减半径/km	斥力增强半径/km
1	13	2.0	300	330	1 500
2	20	-5.0	400	430	1 000
3	28	3.5	400	430	1 300
4	37	-4.0	400	500	1 500