Asymmetrical vortex control device and control method for aircraft forebody

A technology for a control device and an aircraft, applied in the field of fluid control, can solve the problems of poor real-time performance of asymmetric vortex control, multiple payloads, complex structure, etc., and achieve the effects of eliminating asymmetric lateral force, rapid control, and wide application conditions.

Inactive Publication Date: 2012-01-04
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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AI Technical Summary

Problems solved by technology

However, the device has a complex structure, requires a large payload, and has poor real-time control of the asymmetric vortex.

Method used

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  • Asymmetrical vortex control device and control method for aircraft forebody
  • Asymmetrical vortex control device and control method for aircraft forebody
  • Asymmetrical vortex control device and control method for aircraft forebody

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Embodiment Construction

[0015] The technical scheme of the present invention is described in detail below in conjunction with accompanying drawing:

[0016] The idea of ​​the present invention is to use a wall-attached oscillating jet element designed based on the Coanda effect principle to generate oscillating jet flow, and introduce a pressure signal at the jet deflection direction control port of the wall-attached oscillating jet element to change the deflection direction of the jet flow to generate The oscillating jets injected alternately from the blowing ports on both sides of the aircraft can realize the control of the asymmetric vortex of the aircraft precursor, thereby eliminating the lateral force generated by the asymmetric vortex.

[0017] In the 1930s, Romanian scientist Henri-marie Coanda discovered the Coanda effect and made preliminary research on it. The Coanda effect is also known as the Coanda effect. Simply put, the fluid always flows along the curved surface it touches. The rese...

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Abstract

The invention discloses an asymmetrical vortex control device for an aircraft forebody. The device comprises air blowing ports symmetrically arranged at two sides of a leeward area of the aircraft forebody and an oscillating jet device; the oscillating jet device comprises a wall-attached oscillating jet element, a main jet source and a control device; the wall-attached oscillating jet element comprises a jet inlet, a nozzle, a splitter plate, two jet direction deflection control ports and two jet outlets; the main jet source is connected with the jet inlet of the wall-attached oscillating jet element; the air blowing ports are connected with the two jet outlets of the wall-attached oscillating jet element respectively; and the two jet direction deflection control ports of the wall-attached oscillating jet element are connected with the control device respectively. The invention also discloses an asymmetrical vortex control method for the aircraft forebody. The asymmetrical vortex of the aircraft forebody is disturbed by oscillating jet, so that the strength or the position of the asymmetrical vortex of the aircraft forebody is changed. The device has the advantages of simple structure, good instantaneity, no influence on the shape of an aircraft and the like.

Description

technical field [0001] The invention relates to an aircraft precursor asymmetric vortex control device and a control method, which are used for eliminating the asymmetric lateral force generated by the precursor asymmetric vortex when the aircraft flies at a high angle of attack, and belongs to the technical field of fluid control. Background technique [0002] Under the requirements of the future air combat concept, modern high-performance fighter jets or tactical missiles need to have good flight maneuverability and agility. In order to obtain good maneuverability and agility, fighter jets or tactical missiles often need to fly into areas with high angles of attack. A large number of facts and studies have found that when the angle of attack exceeds a certain value, even if the sideslip angle is 0°, the leeward area of ​​the fuselage front will induce a left-right asymmetrical back vortex system, and induce a large lateral The lateral force is accompanied by yaw and rolli...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C17/00B64C21/04
Inventor 史志伟耿玺白亚磊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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