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Aerospace vehicle fairing systems and associated methods

A technology of fairings and aircraft systems, which is applied to aircraft parts, aircraft control, wing lift efficiency, etc., and can solve problems such as fairing resistance

Active Publication Date: 2012-10-10
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, even these fairings create drag on the aircraft

Method used

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  • Aerospace vehicle fairing systems and associated methods
  • Aerospace vehicle fairing systems and associated methods
  • Aerospace vehicle fairing systems and associated methods

Examples

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Embodiment Construction

[0016] The present disclosure describes an aerospace vehicle fairing system and related methods that include a fairing housing a flap surface drive mechanism on an aircraft. In the description below and in the Figure 2-10 Several specific details are set forth in order to provide a thorough understanding of certain embodiments. Those skilled in the art will appreciate, however, that the invention may have additional embodiments, and that other embodiments may be practiced without several of the specific features described below.

[0017] figure 2 An aerospace vehicle 150 is shown having a first fairing system 100a and a second fairing system 100b configured in accordance with an embodiment of the present invention. In some embodiments, the fairing systems 100a and 100b may reduce interference drag and / or increase lift compared to fairings currently used on various aircraft. The features of the first fairing system 100a will be referred to Figure 3-6 are discussed in furt...

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Abstract

erospace vehicle fairing systems and associated methods, including fairings that house flap surface drive mechanisms on aircraft, are disclosed herein. A method in accordance with one embodiment, for example, can include adjusting lift distribution across an airfoil. The airfoil includes a first inboard portion and a second outboard portion. The method can include locating a point of maximum curvature of a first fairing at least approximately forward of a trailing edge of the airfoil proximate to the first inboard portion. The method can also include locating a point of maximum curvature of asecond fairing at least approximately aft of a trailing edge of the airfoil proximate to the second outboard portion. The locations of the points of maximum curvature for the first and second fairings are based, at least in part, on a target lift distribution.

Description

technical field [0001] The present disclosure generally relates to aerospace vehicle fairing systems and related methods, including a fairing housing a flap surface drive mechanism on the vehicle. Background technique [0002] Modern high-speed aircraft typically have thinner wings that provide lower drag when flying at high speeds or when cruising. The wings of these aircraft often include various movable surfaces to provide aircraft control and / or to set up the aircraft for low speed operations such as takeoff and landing. For example, in addition to carrying fuel, the wings of high-speed transport aircraft typically include aileron surfaces, spoiler surfaces, leading-edge equipment surfaces, and trailing-edge flap surfaces. These movable surfaces are often located at or near the leading and trailing edges of the wings, however the wings here are too thin to fully encapsulate the support structures and / or drive mechanisms required to operate these surfaces. Accordingly, ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C7/00B64C9/22B64C9/16
CPCB64C7/00B64C9/16B64C9/22Y02T50/32Y10T29/49622Y02T50/30
Inventor N·沃吉特
Owner THE BOEING CO