宽射程范围可调高速飞行器滑翔制导方法

doi:10.7527/S1000-6893.2025.32903

Abstract

Abstract:

To satisfy the requirements of both maximum and minimum ranges for boost-glide vehicles， an effective and complete gliding guidance method with adjustable wide-range coverage is proposed. Firstly， the characteristics of aerodynamic guidance based on angle of attack and bank angle in the atmosphere are analyzed， and the key difficulties of aerodynamic guidance for different ranges are identified. Secondly， based on the idea of total energy control， the control authorities of velocity and altitude are dynamically allocated in real time. A long-range gliding guidance method based on hybrid energy regulation is proposed to solve the underactuated guidance problem caused by simultaneous control of altitude and velocity via angle of attack. Thirdly， with a fixed angle-of-attack profile， constraints such as load factor and heat flux are transformed into gliding corridor boundaries. On the basis of drag acceleration and altitude feedback， a short-range gliding guidance method with aerodynamic deceleration based on the drag acceleration-velocity profile is designed. Terminal azimuth is constrained within the lateral corridor via on-off control of the bank angle sign. Finally， in long-range and short-range flight simulation verifications， the two guidance methods successfully guide the vehicle to the same terminal window under different range targets， systematically solving the guidance problem of range management for high lift-to-drag ratio vehicles in atmospheric gliding.

Key words: hypersonic vehicles, glide guidance, quasi-equilibrium glide, energy management, drag acceleration-velocity profiles, range management, aerobraking, lift drag ratio

CLC Number:

V448

Zonghua SUN, Xingtai GUAN, Zhengyou WEN, Liaoni WU, Yancheng YOU. Wide-range adjustable glide guidance method for hypersonic vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(12): 332903.

Figures/Tables 26

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参数	数值
质量/kg	1 559
长度/m	8.972
参考面积/m²	0.567 4
最大升阻比	3.3

类型	h_f /km	V_f /（m·s^-1）	θ_f /（°）	Δχ_f /（°）
标称	26.230	1 150.7	-6.39	-0.312
推力上偏	26.024	1 117.1	-6.71	-0.304
推力下偏	26.072	1 129.7	-6.60	-0.308
密度上偏	26.063	1 127.3	-6.67	-0.340
密度下偏	25.557	1 088.8	-7.24	-0.258
法向力上偏	29.169	1 182.8	-5.53	-0.310
法向力下偏	23.338	999.5	-7.23	-0.284
轴向力上偏	24.888	962.5	-8.58	-0.277
轴向力下偏	28.136	1 190.1	-5.32	-0.300
组合上偏	27.441	1 229.4	-4.93	-0.299
组合下偏	23.987	796.7	-12.7	-0.237

类型	h_f/km	V_f/（m·s^-1）	θ_f/（°）	Δχ_f/（°）
推力上偏	25.598	1 132.5	-6.61	-0.315
推力下偏	24.322	1 130.1	-7.13	-0.348
密度上偏	25.794	1 126.8	-6.96	-0.343
密度下偏	24.577	1 113.5	-7.05	-0.291
法向力上偏	28.878	1 137.4	-7.56	-0.312
法向力下偏	13.333	907.4	-13.24	-0.528
轴向力上偏	5.335	406.1	-44.92	-0.773
轴向力下偏	27.723	1 128.6	-7.29	-0.297
组合上偏	27.453	1 139.9	-6.55	-0.278
组合下偏

类型	偏差项	数值（3σ）/%	备注
气动力	轴向力	±15	Ma1
		±8	1≤Ma5
		±5	Ma≥5
	法向力	±5
飞行环境	大气密度	±10	h40 km
		±20	40≤h60 km
		±30	h≥60 km

终端状态	推力标称		推力上偏		推力下偏
终端状态	均值	标准差	均值	标准差	均值	标准差
h_f/m	26.364	0.307	26.034	0.201	26.074	0.179
V_f/（m·s^-1）	1 148.2	8.4	1 117.0	25.7	1 129.0	25.5
θ_f/（°）	-6.28	0.24	-6.72	0.25	-6.58	0.23
Δχ_f/（°）	-0.310	0.491	-0.341	0.529	-0.348	0.507

Wide-range adjustable glide guidance method for hypersonic vehicles

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Figures/Tables 26

References 46

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类型	h_f/km	V_f/（m·s^-1）	θ_f/（°）	Δχ_f/（°）
标称	27.913	1 018.5	-4.97	0.401
推力上偏	28.146	989.9	-3.12	-3.535
推力下偏	27.660	1 016.5	-5.81	2.878
密度上偏	27.718	966.0	-7.02	-4.344
密度下偏	28.025	1 103.6	-1.50	6.291
法向力上偏	27.862	995.2	-5.54	-1.738
法向力下偏	28.122	1 040.0	-3.18	2.484
轴向力上偏	27.908	1 023.2	-5.57	2.418
轴向力下偏	28.003	1 010.0	-3.91	0.490
组合上偏	28.407	1 073.4	-1.12	3.301
组合下偏	27.691	978.6	-6.83	-2.278

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终端状态	推力标称		推力上偏		推力下偏
终端状态	均值	标准差	均值	标准差	均值	标准差
h_f/m	27.948	0.121	28.158	0.101	27.757	0.152
V_f/（m·s^-1）	1 018.0	21.2	991.0	25.8	1 013.9	31.5
θ_f/（°）	-4.73	1.10	-3.12	1.14	-5.13	1.39
Δχ_f/（°）	0.656	1.754	-3.113	2.252	2.730	3.689