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1. 发明申请

US20190241255A1 AIRFLOW INTERRUPTING DEVICES 审中-公开
公开(公告)号：US20190241255A1
公开(公告)日：2019-08-08
申请号：US16270562
申请日：2019-02-07
申请人： Tamarack Aerospace Group, Inc.
发明人： Nicholas R. Guida
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , B64C2003/148 , Y02T50/12 , Y02T50/164
摘要： A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered.

2. 发明申请

US20190225325A1 WING TIP DEVICE ATTACHMENT APPARATUS AND METHOD 审中-公开
公开(公告)号：US20190225325A1
公开(公告)日：2019-07-25
申请号：US16369222
申请日：2019-03-29
申请人： Airbus Operations Limited
发明人： Julien CHAUSSEE , Camille Paumes , Norman Wijker , Stuart Alexander
IPC分类号： B64C23/06 , B64C3/56
CPC分类号： B64C23/072 , B64C3/56 , Y02T50/164 , Y10T29/49826
摘要： A method of assembling a wing tip device to a wing of a powered aircraft including: providing a wing tip, providing a wing tip device, pivotably attaching the wing tip device to the wing at a first position, pivoting the wing tip device about the first position, and attaching the wing tip device to the wing at a second position spaced from the first position.

3. 发明申请

US20190210715A1 Wing Tip With Optimum Loading 审中-公开
公开(公告)号：US20190210715A1
公开(公告)日：2019-07-11
申请号：US16356738
申请日：2019-03-18
申请人： Aviation Partners, Inc.
发明人： Louis B. Gratzer
IPC分类号： B64C23/06 , B64C3/10 , B64C27/46 , B64C11/18
CPC分类号： B64C23/069 , B64C3/10 , B64C11/18 , B64C27/463 , Y02T50/164
摘要： A method for improving performance in an aircraft having a winglet coupled to a wing, the winglet having a leading edge and a trailing edge continuously transitioning from a leading edge and trailing edge of the wing. The method includes coupling a wing tip to the winglet. The wing tip may include a curved leading edge from the winglet leading edge to a leading end point, a curved trailing edge from a winglet trailing edge to a trailing end point, and an end segment connecting the leading end point and the trailing end point. The end segment may be swept back from the trailing end point to the leading end point at an end segment angle.

4. 发明授权

US10053209B2 Aircraft winglet design having a compound curve profile 有权
公开(公告)号：US10053209B2
公开(公告)日：2018-08-21
申请号：US14807579
申请日：2015-07-23
申请人： Stephen R. Speer
发明人： Stephen R. Speer
IPC分类号： B64C23/06 , B64C3/58
CPC分类号： B64C23/065 , B64C23/069 , Y02T50/164
摘要： An improved winglet design is presented for aircraft wherein the winglet configuration is well suited for aircraft wings having moderate to no aft swept, or wings having forward swept. The winglets (302) are located at the outer end of each wing (300) and curve upwardly as they extend outwardly from their intersection (304) with the wings (300). The curvature profile (303) of the winglets (302) when viewed from the rear (or front) of the aircraft at least approximates a specified curve profile made up of more than one curved section, e.g. the winglet trailing edge profile (305) having a perpendicular projection onto a plane normal to the winglet inner or root chord (342), said projection creating a winglet profile curve approximating a compound curve composed of two arc segment (306, 307). The two arc segments are tangent to each other at there point of connection (306b, 307a) wherein the arc segment (306) at the lower portion of the winglet connects to the outer end of the wing (300) and is tangent with the wing's reference plane (331). This lower arc segment (306) of the winglet profile connects to and is tangent with a second arc segment (307) forming the profile of the upper portion of the winglet (302). A unique design specification for the plan form or developed shape of the winglet that is suitable for wings having nominal (less than 15 degrees) aft sweep, or have neutral, or forward sweep is also provided.

5. 发明申请

US20180079493A1 Wing Extension Winglets for Tiltrotor Aircraft 审中-公开
公开(公告)号：US20180079493A1
公开(公告)日：2018-03-22
申请号：US15269862
申请日：2016-09-19
申请人： Bell Helicopter Textron Inc.
发明人： Adam Bryant Anderson , Steven Ray Ivans , Jeremy Robert Chavez
IPC分类号： B64C23/06 , B64C29/00 , B64C3/38
CPC分类号： B64C23/072 , B64C3/385 , B64C23/069 , B64C29/0033 , Y02T50/164
摘要： A pylon assembly for a tiltrotor aircraft includes a rotor assembly operable to rotate between a generally vertical orientation, in a VTOL flight mode, and a generally horizontal orientation, in a forward flight mode, and having an intermediate orientation therebetween, in a conversion flight mode. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension, positioned outboard of the rotor assembly, has a minimal dimension and an outboard end. A winglet is coupled to the outboard end of the wing extension and has a minimal dimension. The wing extension and the winglet are operable to rotate generally with the rotor assembly such that the minimal dimensions of the wing extension and the winglet remain in the slipstream of the proprotor.

6. 发明授权

US09896186B2 Braided composite spar 有权
公开(公告)号：US09896186B2
公开(公告)日：2018-02-20
申请号：US14784977
申请日：2014-04-17
申请人： AIRBUS OPERATIONS LIMITED
发明人： Tony Fong , Timothy Axford
IPC分类号： B64C3/18 , B64C23/06 , B29C70/22 , B29C70/32 , B29C70/30 , B32B38/18 , B64F5/10 , B29L31/30
CPC分类号： B64C3/185 , B29C70/222 , B29C70/30 , B29C70/32 , B29L2031/3085 , B32B38/1866 , B32B2305/72 , B64C23/069 , B64F5/10 , Y02T50/164 , Y02T50/43
摘要： A braided composite spar or preform for a braided composite spar with a plurality of tubular plies of braided fibers. Each ply has a first set of fibers which wind in a clockwise direction in a first series of turns with a pitch between each adjacent pair of turns, and a second set of fibers which wind in an anti-clockwise direction in a second series of turns with a pitch between each adjacent pair of turns. The first and second sets of fibers in each ply are intertwined to form a braided structure. The spar or preform extends lengthwise from a root to a tip and has a tapered portion which tapers inwardly towards the tip. Each ply has a circumference in the tapered portion which reduces as it tapers inwardly. For at least one of the plies the pitches of the first and second sets of fibers increase continuously as the ply tapers inwardly in the tapered portion. The spar or preform can be used to provide a tubular main spar for a winglet. The winglet also has a front spar with a front spar web, an upper front spar cap, and a lower front spar cap. An upper skin of the winglet is joined to the braided spar and the upper front spar cap. A lower skin of the winglet is joined to the braided spar and the lower front spar cap.

7. 发明授权

US09764825B2 Active winglet 有权
公开(公告)号：US09764825B2
公开(公告)日：2017-09-19
申请号：US14222437
申请日：2014-03-21
申请人： Tamarack Aerospace Group, Inc.
发明人： Nicholas R. Guida
IPC分类号： B64C23/06 , B64C13/16
CPC分类号： B64C23/065 , B64C13/16 , B64C23/076 , Y02T50/164
摘要： An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency.

8. 发明申请

US20170203830A1 SPLIT WINGLET 审中-公开
公开(公告)号：US20170203830A1
公开(公告)日：2017-07-20
申请号：US15477940
申请日：2017-04-03
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C5/10 , B64C5/08 , B64C23/06
CPC分类号： B64C5/10 , B64C3/58 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.

9. 发明授权

US09701392B2 Joint 有权
公开(公告)号：US09701392B2
公开(公告)日：2017-07-11
申请号：US15217823
申请日：2016-07-22
申请人： Airbus Operations Limited , Airbus Operations (S.A.S.)
发明人： Rhona Whitlock , Massimo Del Tin , Peter Dalton , George Ford , Michael John Hill , Adrian Huntbatch , Laurence Breeze , Alain Depeige
IPC分类号： B64C3/26 , B64C3/18 , B64C23/06
CPC分类号： B64C3/26 , B64C3/187 , B64C23/069 , Y02T50/164
摘要： A joint including first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

10. 发明申请

US20170152021A1 CONTROLLABLE AIRFLOW MODIFICATION DEVICE PERIODIC LOAD CONTROL 审中-公开
公开(公告)号：US20170152021A1
公开(公告)日：2017-06-01
申请号：US15431719
申请日：2017-02-13
申请人： Tamarack Aerospace Group, Inc.
发明人： Nicholas R. Guida
IPC分类号： B64C13/16 , B64C9/00
CPC分类号： B64C13/16 , B64C23/076 , Y02T50/164 , Y02T50/44
摘要： An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, reduce torsional loads, alleviate flutter, and/or increase efficiency.

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