-
公开(公告)号：US10583910B2
公开(公告)日：2020-03-10
申请号：US15428974
申请日：2017-02-09
申请人： AEROVIRONMENT, INC.
IPC分类号： B64C3/56 , B64C9/36 , B64C5/12 , B64C13/34 , B64C3/44 , B64C3/50 , B64C13/18 , B64C39/02 , B64C9/02 , B64C9/08 , B64C9/18 , B64C11/00 , B64C9/00
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
-
公开(公告)号：US10180027B2
公开(公告)日：2019-01-15
申请号：US15298240
申请日：2016-10-20
摘要： A foldable dual-layered wall structure is positionable in a stowed condition and in a deployed condition. The wall structure includes a first foldable layer having at least a first pair of panels and a first joint rotatably connecting the panels of the at least a first pair of panels. A second foldable layer is positioned adjacent to the first foldable layer. The second foldable layer includes at least a second pair of panels and a second joint rotatably connecting the panels of the at least a second pair of panels. The wall structure is structured such that the first joint is positioned directly opposite a panel of the at least a second pair of panels and the second joint is positioned directly opposite a panel of the at least a first pair of panels when the wall structure is in the deployed condition.
-
公开(公告)号：US20180243972A1
公开(公告)日：2018-08-30
申请号：US15963890
申请日：2018-04-26
申请人： The Boeing Company
IPC分类号： B29C61/06 , B64C3/48 , B29C70/30 , B29C70/88 , B64C3/52 , F03G7/06 , H05K1/16 , B32B15/08 , B29B11/16 , H05K1/05 , B29K267/00 , B29K71/00 , B29C53/82 , B29L31/30 , B64C3/44 , B64C3/54 , B64C27/72
CPC分类号： B29C61/0625 , B29B11/16 , B29C53/822 , B29C70/222 , B29C70/30 , B29C70/32 , B29C70/88 , B29K2071/00 , B29K2267/00 , B29L2031/3085 , B32B15/08 , B32B2250/02 , B32B2605/18 , B64C3/48 , B64C3/52 , B64C2003/445 , B64C2003/543 , B64C2027/7288 , F03G7/065 , H05K1/056 , H05K1/165 , H05K2201/0129 , H05K2201/0308 , Y02T50/34 , Y02T50/43
摘要： Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.
-
公开(公告)号：US10035579B2
公开(公告)日：2018-07-31
申请号：US14859193
申请日：2015-09-18
CPC分类号： B64C3/48 , B63B1/285 , B63B39/06 , B63B41/00 , B63B2039/063 , B63H1/36 , B63H25/382 , B64C3/385 , B64C3/44 , B64C2003/445
摘要： A device for simultaneously and progressively varying the camber and the angle of attack of a hydrodynamic and aerodynamic profile of a wing, the latter being able to adopt multiple positions including a position at rest, the said profile at rest being in a plane, the device having a wing with a profile having a leading edge at the front and a trailing edge at the rear, a seat arranged in the upper part of the profile of the wing connected at one of its ends to the front upper part of the profile by a first pivot, and at its other end to a lever by a connection point, a lever connected to the rear upper part of the profile by a second pivot, and that at rest, a seat and at least one lever are aligned or substantially aligned along the same axis and are included in the same plane as the profile.
-
公开(公告)号：US09821903B2
公开(公告)日：2017-11-21
申请号：US14330824
申请日：2014-07-14
申请人： The Boeing Company
发明人： Abraham J. Pachikara , Matthew A. Moser , Paul H. Carpenter , Michael R. Finn , Thomas S. Koch , Stefan R. Bieniawski , Brian T. Whitehead
CPC分类号： B64C13/16 , B64C3/44 , B64C9/00 , B64C9/12 , B64D45/0005 , G05D1/0825 , Y02T50/32 , Y02T50/44
摘要： Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.
-
公开(公告)号：US20170203829A1
公开(公告)日：2017-07-20
申请号：US15477986
申请日：2017-04-03
申请人： The Boeing Company
CPC分类号： B64C3/185 , B21C37/045 , B64C1/065 , B64C3/44 , B64C27/473 , B64C27/72 , B64C2001/0081 , B64C2027/7211 , C22F1/006 , F03G7/065
摘要： There is provided a training system capable of performing work. The system has a shape memory alloy (SMA) actuator exhibiting a generally planar transformational behavior. The system further has one or more heating elements for transforming the SMA actuator from an original shape to a trained shape, thereby performing work.
-
公开(公告)号：US20170190436A1
公开(公告)日：2017-07-06
申请号：US15374771
申请日：2016-12-09
申请人： David G. Ullman , Vincent Homer
发明人： David G. Ullman , Vincent Homer
CPC分类号： B64D27/24 , B64C3/32 , B64C21/00 , B64D29/02 , B64D31/06 , Y02T50/166 , Y02T50/44 , Y02T50/64
摘要： The Distributed Electric Ducted Fan Wing concept incorporates multiple electric ducted fans on lifting surfaces configured to provide integrated aerodynamics and propulsion resulting in enhanced aerodynamic characteristics and thus aircraft performance. The concept uses a plurality of electric ducted fans (EDFs) to not only provide thrust, but to also blow air across the upper surface of a substantial portion of the lifting surface area increasing lift at little loss in efficiency. Not only can the total lift on the surfaces be enhanced, but the lift distribution managed: to aid in aircraft control; ameliorate the effects of turbulence: reduce shed vortices; mitigate the effects of system failures; eliminate stalls; and compensate for crosswinds. This concept offers the potential for increasing electric airplane efficiency and performance, enhancing Short Takeoff and Landing (STOL) capabilities, improving passenger comfort, and reducing the structural stress and cost of aircraft.
-
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.
-
公开(公告)号：US09457887B2
公开(公告)日：2016-10-04
申请号：US14198012
申请日：2014-03-05
发明人： Robert W. Roe , Umesh N. Gandhi
CPC分类号： B64C3/44 , B64C3/54 , B64C2003/445 , B64C2003/543 , Y02T50/14 , Y10T29/49
摘要： An apparatus and methods for changing the shape of a wing using a trailing edge morphing beam. One example method includes coupling a trailing edge portion comprising a morphing beam to an elastic central portion of the wing. The morphing beam comprises a first portion formed of smart material and a second portion formed of elastic material. The method further includes actuating the smart material in the first portion of the morphing beam to change the shape of the elastic central portion of the wing and the elastic material of the morphing beam. The morphing beam can be configured to hold a first position corresponding to a minimum chord-length of the wing and a second position corresponding to a maximum chord length of the wing.
摘要翻译： 一种用于使用后缘变形光束来改变机翼的形状的装置和方法。 一个示例性方法包括将包括变形光束的后缘部分耦合到翼的弹性中心部分。 变形梁包括由智能材料形成的第一部分和由弹性材料形成的第二部分。 该方法还包括致动变形光束的第一部分中的智能材料以改变翼的弹性中心部分的形状和变形光束的弹性材料。 变形光束可以被配置为保持对应于翼的最小弦长的第一位置和对应于翼的最大弦长的第二位置。
-
公开(公告)号：US08991769B2
公开(公告)日：2015-03-31
申请号：US13751247
申请日：2013-01-28
发明人： Umesh N. Gandhi
CPC分类号： B64C3/36 , B64C3/44 , B64C3/546 , B64C2003/445 , B64C2003/543 , Y10T29/49826
摘要： An apparatus and methods for changing the shape of a wing using a plurality of morphing structures. One example method includes coupling a plurality of morphing structures to each other. Each morphing structure includes an anchor, a plurality of hinges, a plurality of shape-memory alloy members wherein each shape-memory alloy member extends from the anchor to a different hinge, a plurality of springs wherein each spring extends from the anchor to a different hinge, and a plurality of rigid members wherein each rigid member extends between two hinges. The method further includes actuating the plurality of shape-memory alloy members in at least some of the morphing structures wherein the shape-memory alloy members contract when actuated to pull against the hinges and anchors within the actuated morphing structures to rotate the rigid members and change the shape of the actuated morphing structure.
摘要翻译： 一种用于使用多个变形结构来改变机翼的形状的装置和方法。 一个示例性方法包括将多个变形结构彼此耦合。 每个变形结构包括锚，多个铰链，多个形状记忆合金构件，其中每个形状记忆合金构件从锚固件延伸到不同的铰链，多个弹簧，其中每个弹簧从锚固件延伸到不同的 铰链和多个刚性构件，其中每个刚性构件在两个铰链之间延伸。 该方法还包括在至少一些变形结构中致动多个形状记忆合金构件，其中形状记忆合金构件被致动时收缩以抵抗致动变形结构内的铰链和锚定件旋转，从而使刚性构件转动 激活的变形结构的形状。
-
-
-
-
-
-
-
-
-
搜索结果
214 条记录 (耗时 0.03 秒)
