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公开(公告)号：US20190176957A1
公开(公告)日：2019-06-13
申请号：US15838855
申请日：2017-12-12
申请人： The Boeing Company
发明人： Daniel Joseph Braley , Brett I. Lyons , Thomas Joseph Gonze , Trevor E. Tucker , Janet Mary Wick , Eric Eldon Deck , Garrett B. Peters , Nicole Renee Williams , Andrew Lawrence Bauer
CPC分类号： B64C1/36 , B33Y10/00 , B33Y80/00 , B64C1/12 , B64C3/26 , B64C5/02 , B64C5/06 , B64C2001/0072 , H01Q1/287 , H01Q1/36 , H01Q1/52
摘要： Core structures (120) for composite panels (75) of an aircraft (10), composite panels (75) and aircraft (10) including the core structures (120), and methods (200) of manufacturing the composite panels (75) are disclosed herein. The core structures (120) include a first side (140), a second side (150), and a connecting region (160) that interconnects an upper portion (142) of the first side (140) with an upper portion (152) of the second side (150). The first side (140), the second side (150), and the connecting region (160) at least partially define an antenna housing (62), which defines a housing volume (64) configured to contain an aircraft antenna (60) of the aircraft (10), and an electromagnetic wave transmission region (66) configured to permit electromagnetic waves to pass therethrough. The electromagnetic wave transmission region (66) defines a plurality of kite-shaped voids (130) arranged in a repeating pattern and bounded by a corresponding plurality of walls (170), at least 10% of which extends at least substantially perpendicular to a surface (122/124) that bounds the electromagnetic wave transmission region (66).
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公开(公告)号：US20180222570A1
公开(公告)日：2018-08-09
申请号：US15870467
申请日：2018-01-12
申请人： AeroVironment, Inc.
发明人： Christopher Eugene Fisher , Steven Bradley Chambers , Pavil Belik , Austin Craig Gunder , John Peter Zwaan
CPC分类号： B64C5/02 , B64C3/10 , B64C5/06 , B64C9/00 , B64C39/00 , B64C39/024 , B64C39/12 , B64C2201/021 , B64C2201/22
摘要： An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.
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公开(公告)号：US20180086438A1
公开(公告)日：2018-03-29
申请号：US15275596
申请日：2016-09-26
CPC分类号： B64C21/06 , B64C1/16 , B64C5/02 , B64C5/06 , B64C2230/04 , B64D27/18 , B64D27/20 , B64D29/04 , Y02T50/166
摘要： An aircraft is provided including a boundary layer ingestion fan mounted to an aft end of a fuselage. A stabilizer is mounted to the fuselage and extends between a root portion and a tip portion to define a span-wise length and extends between a leading edge and a trailing edge along the longitudinal direction. The stabilizer defines a line of maximum thickness that corresponds to the thickest cross sectional portion of the stabilizer along the span-wise length of the stabilizer. The line of maximum thickness is closer to the leading edge of the stabilizer proximate the root portion than at the tip portion, resulting in a pressure distribution that draws higher velocity air away from an inlet of the boundary layer ingestion fan.
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公开(公告)号：US09914528B2
公开(公告)日：2018-03-13
申请号：US14631423
申请日：2015-02-25
申请人： EMBRAER S.A.
发明人： Helio Hirano , Luis Gustavo Trapp
摘要： Propeller-driven craft (e.g., aircraft) are provided with at least one propulsion system having at least one engine and at least one aerial tractor propeller which generates a propeller propwash airflow when driven by the engine. At least one airfoil is disposed in the propeller propwash airflow of the at least one aerial tractor propeller. The airfoil is contoured and oriented relative to a swirl rotation angle (ω) of the propeller propwash airflow in order to induce a forward force component on the craft in response to the propeller propwash airflow over the at least one airfoil, thus improving the craft's performance and/or reducing fuel consumption.
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5.发明申请公开(公告)号：US20170341774A1
公开(公告)日：2017-11-30
申请号：US15601473
申请日：2017-05-22
申请人： AIRBUS (S.A.S.)
发明人： Mei DING
摘要： The present disclosure relates to a structural component of an aircraft wing body and an aircraft including the structural component. According to an aspect of the present disclosure, a structural component of an aircraft wing body is provided. The structural component includes a body part and a profile. The body part includes an edge portion formed by end portions of a first skin and a second skin of the body part superposed together. The profile is attached to the edge portion. The profile has an outer profile conforming to an outer profile of the body part such that the structural component, as a whole, exhibits an aerodynamic outer profile after the profile is attached to the edge portion. The profile is attached to the edge portion via a plurality of separate intermediate members or by contacting the edge portion.
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公开(公告)号：US09694906B1
公开(公告)日：2017-07-04
申请号：US15132107
申请日：2016-04-18
申请人： KING SAUD UNIVERSITY
发明人： Shereef Aly Sadek
CPC分类号： B64C29/00 , B64C5/06 , B64C25/10 , B64C29/0075 , B64C39/024 , B64C39/08 , B64C39/12 , B64C2201/021 , B64C2201/042 , B64C2201/048 , B64C2201/088 , B64C2201/104 , B64C2201/162 , B64C2201/187
摘要： The vertical takeoff and landing unmanned aerial vehicle includes a pair of selectively rotatable ducted fans and a selectively rotatable thrust vectoring nozzle providing vertical takeoff and landing for an unmanned aerial vehicle or a similar type of aircraft. A pair of fixed forward-swept wings are mounted on a rear portion of a fuselage, and a pair of canards are mounted on a top end of a forward portion of the fuselage. The pair of ducted fans are respectively mounted on free ends of the pair of canards, and are selectively rotatable about an axis parallel to a pitch axis of the fuselage. An engine is mounted in the rear portion of the fuselage, and a thrust vectoring nozzle is mounted on the rear portion of the fuselage for directing thrust exhaust from the engine. The thrust vectoring nozzle is selectively rotatable about an axis parallel to the pitch axis.
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公开(公告)号：US20170121010A1
公开(公告)日：2017-05-04
申请号：US15318536
申请日：2015-06-04
申请人： AIRBUS HELICOPTERS
发明人： Debbie LEUSINK , David ALFANO
摘要： A tail boom having a structure and a protuberance, the protuberance being secure with the structure. In each section of the tail boom, the protuberance extends in elevation over an extension height (Hext) and it extends laterally over an extension thickness (EPext), the extension height (Hext) lying in the range 0.05 times the maximum thickness (EPmax) of the structure, included, to 0.5 times the maximum thickness (EPmax), included, of the section, the extension thickness (EPext) lying in the range 0 to 0.4 times the maximum thickness (EPmax), included, of the section.
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公开(公告)号：US09637218B2
公开(公告)日：2017-05-02
申请号：US14440753
申请日：2013-03-14
摘要： An aircraft includes a propulsor supported within an aft portion of the fuselage. A thrust reverser is supported proximate the propulsor for redirecting thrust forward to slow the aircraft upon landing. A tail extending from the aft portion of the fuselage is angled forward away from the aft portion and out of the discharge of airflow from the thrust reverser.
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9.发明申请公开(公告)号：US20170096214A1
公开(公告)日：2017-04-06
申请号：US15274197
申请日：2016-09-23
发明人： Bruno Stefes , Wolfgang Eilken , Erich Paul
CPC分类号： B64C23/06 , B64C5/06 , B64C9/02 , B64C13/16 , Y02T50/162
摘要： A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed.
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公开(公告)号：US20160297512A1
公开(公告)日：2016-10-13
申请号：US15191527
申请日：2016-06-24
申请人： The Boeing Company
发明人： Eugene A. Dan-Jumbo
CPC分类号： B64C3/20 , B32B3/10 , B32B5/12 , B32B5/26 , B32B7/02 , B32B27/08 , B32B27/20 , B32B27/38 , B32B2262/106 , B32B2307/544 , B32B2307/546 , B32B2307/552 , B32B2307/558 , B32B2603/00 , B32B2605/18 , B64C3/182 , B64C3/185 , B64C5/02 , B64C5/06
摘要： An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment.
摘要翻译： 全复合组件如复合层压飞机后轮具有垂直和水平稳定器，具有不同的层间断裂韧性和不同的刚度，以改善飞行特性。 复合层压板表层结合在一体化和加强的底层结构上以减轻重量并改善损伤容纳。
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