考虑集群尾涡气动耦合效应飞行安全约束的协同制导技术

doi:10.7527/S1000-6893.2023.29906

Abstract

Abstract:

The cooperative attack of clustered aircraft can increase the overall combat effectiveness， however， the dense flight of aircraft faces the flight safety problem caused by the wing wake vortex. Aiming at the aerodynamic coupling effect of the wake vortex in the process of cluster cooperative attack， which can cause the flight safety problem caused by the neighboring aircraft generating too large induced rolling moment， a cooperative attack strategy under the effect of wing wake vortex that can meet the safety constraints of the flight of the aircraft cluster is proposed. A dangerous area model of the wing wake vortex effect during the dense flight of aircraft clusters is established， and the induced speed of the wake vortex and its resulting induced roll moment law are analyzed， on which a wake vortex dangerous area avoidance maneuver strategy based on an improved artificial potential field repulsive function is designed. Based on the consistency error variable of the estimated attack time， the distributed time cooperative guidance law is designed， which ensures that the attack time of all the aircraft can reach the consistency within a finite time， and give a stability proof for the attack time error of the system based on the Lyapunov stability theory. The simulation results show that the proposed cooperative attack strategy considering the flight safety constraints of the wake vortex effect can effectively reduce the influence of the wake vortex interference during the dense flight of the vehicles， which not only ensures the safety of the flight of the aircraft cluster， but also ensures the temporal and spatial consistency of the cooperative attack of the cluster.

Key words: unmanned aerial vehicle, aircraft clusters, cooperative attack, wing wake vortex, aerodynamic coupling effects, flight safety

CLC Number:

V249

Duo ZHENG, Zhichen CHU, Defu LIN, Mingjun WEI, Siyi YUE. Cooperative guidance technique considering flight safety constraints of cluster wake vortex aerodynamic coupling effects[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(18): 329906.

Figures/Tables 30

Fig.1

Fig.2

Table 1

Definitions and values of aircraft parameters

参数	数值
前后飞行器距离d/m	0~100
质量m/kg	10
大气密度 $ρ$ /（kg·m^-3）	1.24
前方飞行器真空速V₁/（m·s^-1）	30
后方飞行器真空速V_f/（m·s^-1）	30
前方飞行器翼展 $B 1$ /m	1
后方飞行器翼展B_f/m	1
机翼特征参数s	$π$ /4
无量纲相对环量系数k	1/6
尾涡消散时间^［13］ $t d i s$ /s	d/V_f
升力线斜率 $C L α$	1
涡核半径 $r c$	0.52 $t d i s$
梢根比 $λ$	0.5
阻尼力矩系数C_Rp	-1

Table 1

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Table 2

Table 3

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目标	位置/m	目标	位置/m
Tgt₁	（4 559，-2 400）	Tgt₆	（4 039，-1 500）
Tgt₂	（4 039，-2 100）	Tgt₇	（3 519，-1 200）
Tgt₃	（3 519，-1 800）	Tgt₈	（4 559，-1 200）
Tgt₄	（4 559，-1 800）	Tgt₉	（4 039，-900）
Tgt₅	（3 000，-1 500）	Tgt₁₀	（4 559，-600）

UAV ID	位置/m	航向角/（°）	视线角/（°）	速度/（m·s^-1）
UAV₁	（0，0）	-10	-27.77	30
UAV₂	（-300，519）	5	-31.12	30
UAV₃	（300，519）	0	-35.77	30
UAV₄	（-600，1 039）	5	-28.83	30
UAV₅	（0，1 039）	-10	-40.24	30
UAV₆	（600，1 039）	5	-36.44	30
UAV₇	（900，1 039）	-10	-40.53	30
UAV₈	（-300，1 559）	5	-29.59	30
UAV₉	（300，1 559）	-10	-33.33	30
UAV₁₀	（0，2 078）	5	-30.43	30

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Cooperative guidance technique considering flight safety constraints of cluster wake vortex aerodynamic coupling effects

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