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split fusion winglet

A technology of winglets and wingtips, applied in the field of aircraft wings, can solve problems such as increasing the wing bending moment

Active Publication Date: 2019-11-15
AVIATION PARTNERS INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

While winglets reduce drag from wingtip vortices, winglets create lift, increasing the bending moment on the wing

Method used

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Embodiment Construction

[0049] In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. In other cases, specific numerical references may be made, such as "first winglet". However, specific numerical references should not be construed as a literal ordinal order, but rather that a "first winglet" is different from a "second winglet". Accordingly, the specific details set forth are examples only. Specific details may be varied and still be contemplated within the spirit and scope of the invention. The term "coupled" is defined to mean directly connected to a component or indirectly connected to a component through another component. Furthermore, as used herein, the term "about", "approximately" or "substantially" for any numerical value or range indicates a suitable value that allows a p...

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Abstract

The present invention provides a split winglet configured to be attached to the wing of an aircraft. The split winglet may include an upper winglet extending smoothly from the wingtip above a chord plane of the wing, and a pelvic fin protruding from a lower surface of the upper winglet below the chord plane. The upper winglet may include a transition portion that curves upwardly from the wing tip to a generally flat portion. The upper and lower surfaces of the upper winglet may be bounded by leading and trailing edges swept toward the direction of airflow, parallel to the chord plane, and curved toward the direction of airflow, terminating at A little bit distal to the wing tip. Similarly, the upper and lower surfaces of the pelvic fin may be bounded by leading and trailing edges that are curved towards the direction of the airflow and terminate at a point distal to the wing tip.

Description

[0001] priority [0002] This application claims priority and benefit to U.S. Patent Application No. 14 / 452,424, filed August 5, 2014, which is a continuation-in-part of U.S. Patent Application No. 12 / 488,488, filed June 19, 2009, which The U.S. Patent Application claims the benefit of U.S. Provisional Application No. 61 / 074,395, filed June 20, 2008; and is also a continuation-in-part of U.S. Patent Application No. 13 / 493,843, filed June 11, 2012, which The application claims the benefit of US Provisional Application No. 61 / 495,236, filed June 9, 2011. Each of the aforementioned applications is incorporated by reference into this application in its entirety. technical field [0003] The present application relates to the field of aircraft, and more particularly, to aircraft wings. Background technique [0004] All aircraft wings experience resistance as they move through the air. The drag experienced can be divided into three components: induced drag, parasitic drag, and...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C23/06
CPCB64C23/069Y02T50/10Y02E10/72B64C23/065
Inventor L·B·格拉泽
Owner AVIATION PARTNERS INC
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