基于升阻比-速度剖面的解析再入制导方法

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

系统仿真学报 ›› 2026, Vol. 38 ›› Issue (3): 651-669.doi: 10.16182/j.issn1004731x.joss.25-0855

• 论文 • 上一篇

基于升阻比-速度剖面的解析再入制导方法

孙伟博¹^,²^,³, 马萍¹^,², 王玉轩⁴, 王松艳¹^,², 晁涛¹^,²

^1.哈尔滨工业大学控制与仿真中心，黑龙江哈尔滨 150080
^2.复杂系统建模与仿真全国重点实验室，黑龙江哈尔滨 150080
^3.北京控制与电子技术研究所，北京 100038
^4.空基信息感知与融合全国重点实验室，河南洛阳 471009

收稿日期:2025-09-05 修回日期:2025-10-07 出版日期:2026-03-18 发布日期:2026-03-27
通讯作者: 晁涛
第一作者简介:孙伟博(1994-)，男，博士，研究方向为高超声速飞行器任务规划与制导控制。
基金资助:
国家自然科学基金(62273119);航空科学基金联合资助项目(20240001077001)

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

Sun Weibo¹^,²^,³, Ma Ping¹^,², Wang Yuxuan⁴, Wang Songyan¹^,², Chao Tao¹^,²

^1.Control and Simulation Center, Harbin Institute of Technology, Harbin 150080, China
^2.National Key Laboratory of Modeling and Simulation for Complex Systems, Harbin 150080, China
^3.Beijing Institute of Control & Electronic Technology, Beijing 100038, China
^4.National Key Laboratory of Air-based Information Perception and Fusion, Luoyang 471009, China

Received:2025-09-05 Revised:2025-10-07 Online:2026-03-18 Published:2026-03-27
Contact: Chao Tao

摘要/Abstract

摘要：

针对高超声速滑翔飞行器再入过程中的飞行时间精确控制与禁飞区规避问题，提出了一种基于升阻比-速度剖面的解析再入制导方法。对再入运动模型进行降阶处理，利用切比雪夫级数近似非线性积分项与微分方程，建立滑翔轨迹的解析表达式；推导飞行时间、待飞航程与升阻比-速度剖面之间的解析关系，将升阻比-速度剖面优化问题转化为攻角-速度剖面的分段参数优化问题。通过在线更新机制实时调整升阻比剖面，并结合基于改进人工势场法的自适应侧向制导律，在满足常规再入约束的同时，满足飞行时间约束和禁飞区约束。仿真结果表明：该方法能够有效协调多飞行器的末段到达时序，并成功规避多个禁飞区。

关键词: 高超声速滑翔飞行器, 升阻比-速度剖面, 解析再入制导, 禁飞区约束, 时间约束

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

中图分类号:

TP448.2

孙伟博,马萍,王玉轩等 . 基于升阻比-速度剖面的解析再入制导方法[J]. 系统仿真学报, 2026, 38(3): 651-669.

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

图/表 28

图1

图2

图3

图4

图5

图6

图7

图8

表1

无禁飞区场景下终端状态误差

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

表1

表2

表3

图9

图10

图11

图12

表4

表5

表6

表7

图13

图14

图15

图16

表8

飞行器初始状态

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

表8

表9

图17

图18

表10

终端待飞航程与终端飞行时间误差

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

表10

参考文献 33

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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

基于升阻比-速度剖面的解析再入制导方法

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

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