Synthetic jet circulation control method for increasing wing lifting force

A technology of synthetic jet flow and circulation control, which is applied to wings, aircraft parts, jet power plants, etc., can solve the problems of complex structure and the need for gas source pipelines, and achieve the effects of rapid response, compact structure, and light weight

Inactive Publication Date: 2011-08-31
BEIHANG UNIV
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  • Description
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Problems solved by technology

[0006] 1. Purpose: The purpose of the present invention is to provide a synthetic jet circulation control method that improves wing lift, which overcomes the defici

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  • Synthetic jet circulation control method for increasing wing lifting force
  • Synthetic jet circulation control method for increasing wing lifting force
  • Synthetic jet circulation control method for increasing wing lifting force

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Embodiment Construction

[0042] see Picture 10 , The present invention is a synthetic jet circulation control method for improving wing lift. The specific steps of the method are as follows:

[0043] Step 1: Select a synthetic jet actuator (piston type or piezoelectric film type synthetic jet actuator). The average jet velocity is required to be about 5~280m / s, and the excitation frequency, output waveform, blowing and suction of the synthetic jet actuator Ratio is adjustable. reference figure 1 with figure 2 The piezoelectric thin-film synthetic jet actuator shown in is composed of a piezoelectric ceramic film, a cavity of a slit or a small hole. When the actuator is turned on, the piezoelectric ceramic drives the diaphragm to vibrate, causing the air in the cavity to move from the slit or The small holes reciprocate in and out, and the blowing / inhalation of the slits or small holes forms a series of vortex pairs or vortex rings outside the exciter (two-dimensional slits form vortex pairs, and circu...

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Abstract

The invention discloses a synthetic jet circulation control method for increasing wing lifting force, and the method provided by the invention comprises the following four steps: (1) selecting applicable synthetic jet exciters; (2) arranging a slit tangent to a wing section or a wing surface on a Coanda surface at the rear edge of the wing section or the wing surface; (3) on the Coanda surface at the rear edge of the wing section or the wing surface, arranging the synthetic jet exciters in various forms; and (4) according to different arrangement manners of the synthetic jet exciters, carrying out different controls on the wing section or an airplane, thus achieving the purposes of increasing or decreasing wing lifting force or realizing the airplane rolling control. In the invention, the synthetic jet is utilized to replace the traditional continuous jet, the method has the characteristic of external output momentum only and zero output quality, neither a gas source nor a pipeline system is required, and the defect that the traditional blowing type circulation control structure is complicated is solved. The method has better practical value and wide application prospect in the technical field of aviation flow control.

Description

(1) Technical field: [0001] The present invention relates to a synthetic jet circulation control method, in particular to a synthetic jet circulation control method for improving the lift of a wing, which can be applied to the Coanda surface of the wing or the trailing edge of the airfoil to replace the traditional blowing type The role of the synthetic jet circulation control method to increase aircraft lift or provide flight control. It belongs to the technical field of aviation flow control. (2) Background technology: [0002] The circulation control technology is derived from the Coanda effect. The main principle is to use the Coanda effect of the fluid on the curved surface shape to delay the separation of the boundary layer through the Coanda effect of the tangential jet at the trailing edge of the airfoil, thereby changing the stagnation point position of the trailing edge of the airfoil, which can greatly improve The lift of the airfoil, the maximum increase efficiency ...

Claims

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Application Information

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IPC IPC(8): B64D27/18B64C3/32
Inventor 张攀峰王晋军燕波巴玉龙戴晨峰
Owner BEIHANG UNIV
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