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公开(公告)号：US20180281926A1
公开(公告)日：2018-10-04
申请号：US15614834
申请日：2017-06-06
申请人： The Boeing Company
摘要： An aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The strut comprises a strut inboard end portion and a strut outboard end portion. The strut inboard end portion is coupled to and extends from the body and the strut outboard end portion is coupled to and extends from the intermediate portion of the wing. The strut outboard end portion of the strut is configured to generate a download acting on the strut outboard end portion of the strut when the aircraft is in flight.
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2.发明申请公开(公告)号：US20230140102A1
公开(公告)日：2023-05-04
申请号：US17452973
申请日：2021-10-29
申请人： The Boeing Company
发明人： Robert E. Grip , Neal A. Harrison
摘要： An aircraft includes a fuselage and a pair of wings. Each wing is coupled to the fuselage at a wing-fuselage joint, and is supported by a strut coupled to the fuselage at a strut-fuselage joint and coupled to the wing at a strut-wing joint. The strut-fuselage joint is located below and at least partially aft of the wing-fuselage joint. The wing generates a lifting force when air passes over the wing. The lifting force induces a vertical moment about the wing-fuselage joint due to the location of the strut-fuselage joint below and at least partially aft of the wing-fuselage joint. The wing and/or the strut has a structural arrangement configured to counteract the vertical moment.
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公开(公告)号：US10933970B2
公开(公告)日：2021-03-02
申请号：US15938209
申请日：2018-03-28
申请人： THE BOEING COMPANY
发明人： Neal A. Harrison , Anthony J. Sclafani , Christopher K. Droney , Lie-Mine Gea , David S. Lazzara
摘要： An aircraft includes a body, a wing coupled to and extending from the body, and a strut. The wing includes a wing thickest region bounded by a wing thickest region leading boundary and a wing thickest region trailing boundary. The strut includes a strut thickest region bounded by a strut thickest region leading boundary and a strut thickest region trailing boundary. In a planform view, the wing thickest region overlaps the strut thickest region at an overlap region, where the overlap region including less than fifteen percent of the strut thickest region.
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公开(公告)号：US09598167B2
公开(公告)日：2017-03-21
申请号：US14196461
申请日：2014-03-04
申请人： The Boeing Company
摘要： An airfoil may include a leading edge and a shape control mechanism. The leading edge may include a flexible leading edge skin having a first end, a second end, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations and may transition the flexible leading edge skin from a first shape having a first curvature profile to a second shape having a second curvature profile different than the first curvature profile without a change in the arc length.
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公开(公告)号：US10974808B2
公开(公告)日：2021-04-13
申请号：US15928429
申请日：2018-03-22
申请人： The Boeing Company
发明人： Neal A. Harrison , Lie-Mine Gea , Anthony J. Sclafani , Eric D. Dickey , Michael D. Beyar , Christopher K. Droney
摘要： Described herein is an aircraft. The aircraft comprises a body. The aircraft also comprises a wing coupled to and extending from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The aircraft further comprises a strut. The strut comprises a strut inboard end portion coupled to and extending from the body and a strut outboard end portion coupled to and extending from the intermediate portion of the wing. The aircraft additionally comprises at least one aerodynamic control surface movably coupled to the strut.
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公开(公告)号：US10556666B2
公开(公告)日：2020-02-11
申请号：US15476089
申请日：2017-03-31
申请人： The Boeing Company
摘要： Disclosed herein is an aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. A strut inboard end portion is coupled to and extends from the body and a strut outboard end portion is coupled to and extends from an intermediate portion of the wing. The wing further comprises a first thinned portion adjacent the intermediate portion of the wing. An overall thickness of the first thinned portion of the wing decreases and increases in a spanwise direction along the wing. The strut further comprises a second thinned portion adjacent the outboard end portion of the strut. An overall thickness of the second thinned portion of the strut decreases and increases in a spanwise direction along the strut.
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公开(公告)号：US20180281922A1
公开(公告)日：2018-10-04
申请号：US15476089
申请日：2017-03-31
申请人： The Boeing Company
摘要： Disclosed herein is an aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. A strut inboard end portion is coupled to and extends from the body and a strut outboard end portion is coupled to and extends from an intermediate portion of the wing. The wing further comprises a first thinned portion adjacent the intermediate portion of the wing. An overall thickness of the first thinned portion of the wing decreases and increases in a spanwise direction along the wing. The strut further comprises a second thinned portion adjacent the outboard end portion of the strut. An overall thickness of the second thinned portion of the strut decreases and increases in a spanwise direction along the strut.
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公开(公告)号：US20160031550A1
公开(公告)日：2016-02-04
申请号：US14448479
申请日：2014-07-31
申请人： The Boeing Company
CPC分类号： B64C23/06 , B64C1/0009 , B64C19/00 , B64C21/02 , B64C2230/08 , B64C2230/20 , B64C2230/22 , B64C2230/24 , F15D1/0025 , Y02T50/12 , Y02T50/162 , Y02T50/166
摘要： A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow.
摘要翻译： 涡流发生器可以包括空气动力学表面中的凹陷和位于凹陷中的涡流发生器前缘。 涡流发生器前缘可以包括前缘上表面。 前缘上表面可以定位在相对于迎面而来的局部流动沿着凹陷上游的空气动力学表面的位置处的切线处或下方。
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9.发明授权公开(公告)号：US11787524B2
公开(公告)日：2023-10-17
申请号：US17452973
申请日：2021-10-29
申请人： The Boeing Company
发明人： Robert E. Grip , Neal A. Harrison
CPC分类号： B64C1/26 , B64C3/14 , B64C3/16 , B64C2003/149
摘要： An aircraft includes a fuselage and a pair of wings. Each wing is coupled to the fuselage at a wing-fuselage joint, and is supported by a strut coupled to the fuselage at a strut-fuselage joint and coupled to the wing at a strut-wing joint. The strut-fuselage joint is located below and at least partially aft of the wing-fuselage joint. The wing generates a lifting force when air passes over the wing. The lifting force induces a vertical moment about the wing-fuselage joint due to the location of the strut-fuselage joint below and at least partially aft of the wing-fuselage joint. The wing and/or the strut has a structural arrangement configured to counteract the vertical moment.
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公开(公告)号：US10967957B2
公开(公告)日：2021-04-06
申请号：US15385444
申请日：2016-12-20
申请人： The Boeing Company
摘要： Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.
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