飞翼布局飞机耦合运动失稳的主动流动控制

doi:10.7527/S1000-6893.2022.27353

Abstract

Abstract: Flying-wing aircraft is an important configuration for modern aircraft design. Due to the lack of traditional control surfaces such as horizontal tails and vertical tails, the flying-wing aircraft may encounter a serious of dynamic problems at high angles of attack, such as roll instability, coupled pitch-roll instability, and coupled yaw-roll instability, affecting the aerodynamic performance and flight safety. To address this issue, this study of synthetic jet active flow control is conducted. The control strategy of enhancing leading-edge vortex to improve stability is proposed. The effect of the synthetic jet on the control law of the roll motion and its coupled motion is analyzed, and the flow control mechanism of the synthetic jet under dynamic motion and the coupled effect revealed. It is indicated that the synthetic jet positioned at the leading edge of the flying-wing aircraft can effectively enhance the leading-edge vortex, thereby changing the aerodynamic force and moment. A control strategy is proposed to ensure that the control moment vector is always opposite to the angular velocity of the roll motion, which can increase the roll damping, thereby improving the lateral stability. The present results can provide an important technical support for the stabilization control of the flying-wing aircraft.

Key words: flying-wing aircraft, coupled motion, instability, synthetic jet, dynamic control

CLC Number:

V211.7

FENG Lihao, WEI Lingyun, DONG Lei, WANG Jinjun. Active flow control for coupled motion instability of flying-wing aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(10): 527353-527353.

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Active flow control for coupled motion instability of flying-wing aircraft

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