Unsteady small-perturbation control device for synthetic jet of asymmetric vortices at high attack angle

Abstract

The invention discloses an unsteady small-perturbation control device for a synthetic jet of asymmetric vortices at high attack angle. The unsteady small-perturbation control device comprises a synthetic jet outlet, a needle tube type hollow structure, a synthetic jet exciter cavity body, a speaker diaphragm, a power amplifier and a signal generator, wherein the output end of the signal generator is connected with the input end of the power amplifier, an output end driving signal of the power amplifier is connected with the synthetic jet exciter cavity body and the speaker diaphragm, the speaker diaphragm is fixedly mounted at the synthetic jet exciter cavity body, the needle tube type hollow structure is connected with the opening of the synthetic jet exciter cavity body, and the synthetic jet outlet is arranged at the other end of the needle tube type hollow structure. The control device can regulate and control parameters, such as perturbation control frequency of the synthetic jet, and the like according to actual needs, so as to achieve the aim of controlling the asymmetric vortices at high attack angle and proportionally controlling a lateral force by low energy consumption.

Description

technical field [0001] The invention belongs to the field of aerospace vehicle control, in particular to a frequency controllable unsteady small disturbance active flow control device, which can be used to realize the active control of the asymmetrical back vortex / lateral force of the precursor when the aircraft flies at a large angle of attack. Background technique [0002] In order to obtain good high maneuverability and agility, modern fighter jets often have a flight angle of attack that reaches a large range of angle of attack, and sometimes even exceeds the maximum lift angle of attack. When the angle of attack exceeds a certain value, even in the case of no sideslip angle, a very complex left and right asymmetric back vortex system will be formed in the leeward area of ​​the fuselage front, inducing a large lateral force, accompanied by Yaw and roll moments, and the law of lateral force magnitude and direction change is unpredictable. The efficiency of conventional...

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Problems solved by technology

[0005] (1) Although the head side strip can restrain the amplitude of the lateral force to a certain extent, it will cause additional waste resistance and structural weight gain;

[0006] (2) Although the rotatable head can effectively determine and change the direction of the lateral force, it cannot control and eliminate the lateral force;

[0007] (3) The direction of the lateral force and the size of the lateral force can be changed within a certain range by using the head blowing and suction control technology, but the lateral force cannot be completely eliminated; in addition, the blowing and suction system requires additional air Sources, pipelines and control valves will also cause a series of problems such as additional weight gain, energy consumption and system reliability. The ratio of high cost to benefit is very unreasonable

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