Synthetic jet exciting device and wingtip vortex control method

Abstract

The invention provides a synthetic jet exciting device and a wingtip vortex control method. The synthetic jet exciting device comprises a shell body, a first magnet and a second magnet; a channel is formed in the shell body, the shell body is wound with a metal coil, and the two ends of the metal coil are electrically connected with an output end of an alternating current power source; the first magnet and the second magnet are located at the position, in the channel of the shell body, of the winding position of the metal coil, and a rubber film is clamped between the first magnet and the second magnet; and the channel in the shell body is divided into a first channel and a second channel by the rubber film, and the first channel and the second channel do not communicate with each other. When the metal coil communicates with the alternating current power source, the first magnet and the second magnet clamp the rubber film to conduct reciprocating motion in the channel of the shell body under the control of an alternating current electric field. The synthetic jet exciting device cannot add excessive weight to wings, the outlines of the wings are not changed, meanwhile no additional gas source needs to be added, and the device is simple in structure and small in size, makes small vibration on the wings, and array layout can be conducted in the wings easily.

Description

technical field [0001] The invention relates to the technical field of fluid transmission and flow control, in particular to a synthetic jet excitation device and a wingtip vortex control method. Background technique [0002] During the flight of the aircraft, a pair of counter-rotating wingtip vortices are drawn from the wingtips. The wingtip vortex is the most important flow structure in the wake of a fixed-wing aircraft, and it will remain stable for a period of time in the airspace after the aircraft flies by, thereby causing up / down washing disturbances to the environmental flow field and seriously affecting the flight safety of the trailing aircraft. The attenuation time of the wingtip vortex over the runway determines the minimum time interval for the subsequent aircraft to take off and land. Therefore, the flow control technology can reduce the strength of the wing tip vortex and accelerate the attenuation of the wing tip vortex. [0003] At present, there are two ...

AI Technical Summary

Problems solved by technology

[0004] However, the above-mentioned traditional synthetic jet actuators have their own shortcomings, for example: piezoelectric ceramic actuators with very small additional mass have short fatigue life; connecting rod piston actuators with high reliability have additional mass and large volume, it is difficult to achieve stable and precise control of jet flow; plasma actuators have problems such as large power consumption and difficulty in obtaining airworthiness certificates

Therefore, the current synthetic jet actuators cannot simultaneously meet the requirements of low additional mass, no additional gas source, and flexible adjustment

Images