基于环量控制的无尾飞翼俯仰和滚转两轴无舵面姿态控制飞行试验

doi:10.7527/S1000-6893.2022.28224

Abstract

Abstract:

The circulation control is efficient for rudderless flight control by driving the compressed air jet to generate a virtual rudder surface， which significantly improves low detectability. A closed-loop control strategy based on the terminal pressure feedback of the actuator is proposed， and an airborne multi-channel closed-loop control jet actuation system is independently developed， which was fused into flight control system， realized closed loop attitude control based on active jet. Based on the UAV with tailless flying wing configuration， in a fully autonomous flight control mode， the capability of circulation control for pitch and roll attitude control is quantitatively studied through the flight test at 60 m/s cruising speed. The results show that the combination of circulation actuator channels is available for bidirectional continuous and stable control of pitch and roll control torque. The results also show that the response delay of the jet-actuation system is less than 0.02 s， the response time of the jet-actuated UAV at the attitude angle velocity is less than 0.02 s； the pressure ratio -1.025 of the pitch circulation actuator is equivalent to the pitching moment generated by the elevator at -2.5° rudder angle， and the pressure ratio 1.050 of the roll circulation actuator is equivalent to the rolling moment generated by the aileron at 2.0° rudder angle， so as to realize rudderless attitude control in longitudinal and lateral attitude respectively.

Key words: circulation control, active flow control, flight test, flying wing, closed-loop control, jet actuation system

CLC Number:

V211

Liu ZHANG, Yong HUANG, Fuzheng CHEN, Zhenglong ZHU, Tianhao GUO, Yubiao JIANG, Zhu ZHOU. Rudderless attitude control flight test based on circulation control of tailless flying wing in pitch and roll axes[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(18): 128224-128224.

Figures/Tables 13

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Table 1

Table 2

Control strategy of jet channel combination

射流舵面	功能	左激励器	右激励器	压力关系
射流升降舵	低头力矩	A状态	A状态	δ_p_L=δ_p_R
	抬头力矩	B状态	B状态
射流副翼	右滚力矩	A状态	B状态	$δ p L$ = $δ p R$
	左滚力矩	B状态	A状态

Table 2

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

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参数	数值
机长L/m	1.696
翼展b/m	3.00
平均气动弦长c/m	0.986
参考面积S/m²	1.966 8
质量（满油）m/kg	65.0
X轴转动惯量I_x/（kg·m²）	10.455
Y轴转动惯量I_y/（kg·m²）	8.373
Z轴转动惯量I_z/（kg·m²）	17.775

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Rudderless attitude control flight test based on circulation control of tailless flying wing in pitch and roll axes

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