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Active systems and methods for controlling an airfoil vortex

A technology of wing and vortex, applied in the field of controlling the vortex of aircraft, can solve problems such as unsuitable practical application

Active Publication Date: 2008-03-05
THE BOEING CO
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, many proposed schemes have proven to be ineffective or unsuitable for practical applications

Method used

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  • Active systems and methods for controlling an airfoil vortex
  • Active systems and methods for controlling an airfoil vortex
  • Active systems and methods for controlling an airfoil vortex

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Embodiment Construction

[0032] Aspects of the present disclosure include airfoil vortex dissipation systems and related methods relating to the systems. Wings incorporating the present system generally have a leading edge, a trailing edge, an outer end, an upper aerodynamic surface, a lower aerodynamic surface, a span axis, a front to aft chord axis, and an alignment reference plane coincident with the span axis and the chord axis . When the airfoil is used to generate aerodynamic lift, a vortex is created at the outer end of the airfoil (eg, the wingtip of the airfoil). The vortex has a vortex axis, a main circumferential flow region and a peripheral flow region.

[0033] In one embodiment, the swirl dissipating device includes a nozzle portion located at or adjacent to the outer end of the airfoil and having a nozzle discharge portion, in this embodiment the nozzle discharge portion is in a generally forward to aft direction, located at or Alignment near the outer end of the wing. The nozzle por...

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Abstract

Active systems and methods for controlling aircraft vortices are disclosed. An apparatus (50) in accordance with one embodiment is directed to an aircraft system that includes an airfoil (14) having first and second oppositely facing flow surfaces (23,24) and a tip (20). The system can further include a vortex dissipation device (50) carried by the airfoil (14), with the vortex dissipation device (14) including an orifice (66) positioned to direct a flow of fluid outwardly from the tip (20), an actuator (92) operatively coupled to the fluid flow orifice and positioned to change a manner in which flow is directed outwardly from the tip (20), and a controller operatively coupled to the actuator to direct the operation of the actuator. The vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated, for example, by alternately pulsing flow inwardly and outwardly through the fluid flow orifice.

Description

[0001] Cross References to Related Applications [0002] This application also claims priority to US Provisional Application No. 60 / 840,121, filed August 25, 2006, the contents of which are incorporated herein by reference. technical field [0003] The present disclosure generally relates to systems and methods for controlling aircraft vortices. Background technique [0004] Current airport capacity is largely constrained by operating hours (which are largely limited by daylight hours to prevent noise pollution to the airport environment) and the frequency of aircraft entering and leaving the port. A major factor affecting the frequency of landings and takeoffs is the time required to dissipate the wake vortices created by a moving aircraft. The size and strength of the wake vortex is determined by the size and weight of the aircraft, which can create turbulent conditions in the wake of a wide-body aircraft. In worst-case scenarios, these vortices are powerful enough to cr...

Claims

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Application Information

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IPC IPC(8): B64C23/00B64C3/58
CPCY02T50/164B64C23/065B64C23/076Y02T50/10
Inventor 阿尔文·施米洛维奇约拉姆·亚德林罗杰·W·克拉克
Owner THE BOEING CO
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