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81. 发明授权

US09896200B2 Vertical takeoff and landing vehicle with increased cruise efficiency 有权
公开(公告)号：US09896200B2
公开(公告)日：2018-02-20
申请号：US15332391
申请日：2016-10-24
申请人： The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
发明人： William J. Fredericks , Mark D. Moore , Ronald C. Busan , Paul M. Rothhaar , David D. North , William M. Langford , Christopher T. Laws , William T. Hodges , Zachary R. Johns , Sandy R. Webb
IPC分类号： B64C29/00 , B64C39/00 , B64C11/28 , B64C25/52 , B64D27/24 , B64C3/40 , B64C9/14 , B64D27/26 , B64C11/50 , B64C25/32 , B64C3/38 , B64C39/02 , B64C5/02 , B64D27/02
CPC分类号： B64C29/0033 , B64C3/385 , B64C3/40 , B64C5/02 , B64C9/14 , B64C11/28 , B64C11/50 , B64C25/32 , B64C25/52 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/044 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/165 , B64D27/24 , B64D27/26 , B64D2027/026 , Y02T50/44 , Y02T50/64 , Y10S903/903
摘要： Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

82. 发明申请

US20170369151A1 METHODS OF CONFIGURING A WING TIP DEVICE ON AN AIRCRAFT 审中-公开
公开(公告)号：US20170369151A1
公开(公告)日：2017-12-28
申请号：US15629013
申请日：2017-06-21
申请人： Airbus Operations Limited
发明人： Robert Ian THOMPSON , Geoffrey Richard WILLIAMS , Nicholas LIVINGS , Kevin NICHOLLS
IPC分类号： B64C3/56 , B64C3/58 , B64C3/40
CPC分类号： B64C3/56 , B64C3/40 , B64C3/58 , Y02T50/14
摘要： A method of configuring a wing tip device (7) on an aircraft (1), including: undertaking ground-based operations at an airport with the wing tip device (7) in a ground configuration, in which the span of the aircraft is within an airport compatibility limit, moving the wing tip device (7) to a take-off configuration in which the wing tip device (7) is moved away from the ground configuration such that the span of the aircraft is increased and such that the wing tip device (7) has a first lift coefficient; taking-off with the wing tip device (7) in the take-off configuration; moving the wing tip device from the take-off configuration to a flight configuration, in which the wing tip device has a second lift coefficient, the second lift coefficient being lower than the first lift coefficient. The lift coefficient may be changed by adjusting the sweep of the wing tip device (7).

83. 发明授权

US09718534B2 Aircraft lifting surface with variable sweep distribution along the span 有权
公开(公告)号：US09718534B2
公开(公告)日：2017-08-01
申请号：US13942880
申请日：2013-07-16
申请人： Airbus Operations S. L.
发明人： Angel Pascual Fuertes , Sergio Rodriguez Sanchez
IPC分类号： B64C3/38 , B64C3/40 , B64C5/02 , B64C5/04 , B64C39/12 , B64C3/10
CPC分类号： B64C3/40 , B64C3/10 , B64C5/02 , B64C5/04 , B64C39/12
摘要： An aircraft lifting surface attached to the rear or frontal end of the aircraft fuselage with a variable sweep angle α in an inboard part and with a constant sweep angle α1 in an outboard part. The aircraft lifting surface can be for example a horizontal tail plane or a vertical tail plane attached to the rear end fuselage or a canard attached to the frontal end fuselage.

84. 发明授权

US09475579B2 Vertical take-off and landing vehicle with increased cruise efficiency 有权
标题翻译：垂直起降车辆，提高巡航效率
公开(公告)号：US09475579B2
公开(公告)日：2016-10-25
申请号：US14121001
申请日：2014-08-13
申请人： The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
发明人： William J. Fredericks , Mark D. Moore , Ronald C. Busan , Paul M. Rothhaar , David D. North , William M. Langford , Christopher T. Laws , William T. Hodges , Zachary R. Johns , Sandy R. Webb
IPC分类号： B64D27/24 , B64D27/26 , B64C29/00 , B64C3/40 , B64C9/14 , B64C11/50 , B64C25/32 , B64C3/38 , B64C39/02 , B64D27/02
CPC分类号： B64C29/0033 , B64C3/385 , B64C3/40 , B64C5/02 , B64C9/14 , B64C11/28 , B64C11/50 , B64C25/32 , B64C25/52 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/044 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/165 , B64D27/24 , B64D27/26 , B64D2027/026 , Y02T50/44 , Y02T50/64 , Y10S903/903
摘要： Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.
摘要翻译：提供了系统，方法和装置，其将先进的车辆配置（例如先进的飞行器配置）与电力推进的输注结合在一起，从而能够在保持完全垂直起飞和着陆的同时保持四倍的范围和耐力增加（“VTOL “）和车辆的悬停能力。实施例可以提供具有垂直起落架和巡航高效能力的车辆，而不使用地面基础设施。一种实施方式的车辆可以包括被配置为倾斜运动范围的翼，连接到翼的第一系列电动马达，并且每个被配置成驱动相关翼翼推进器，构造成在所述运动范围内倾斜的尾部，第二系列耦合到尾部并且每个被配置为驱动相关联的尾部螺旋桨的电动马达以及连接到第一系列电动机和第二系列电动机的电推进系统。

85. 发明授权

US09296468B1 Aerial vehicle with separation of winged surfaces in first and second flexed states 有权
标题翻译：在第一和第二弯曲状态下分离有翼表面的飞行器
公开(公告)号：US09296468B1
公开(公告)日：2016-03-29
申请号：US14032800
申请日：2013-09-20
申请人： Brandebury Tool Company, Inc.
发明人： William B. Harvey , Matthew G. Amsellem
IPC分类号： B64C3/40 , B64C39/02
CPC分类号： B64C3/40 , B64C39/024 , B64C2201/028 , B64C2201/102
摘要： Embodiments include an aerial vehicle. Two winged surfaces are provided in communication with a fuselage. The surfaces are in communication at a front edge via a cuff, at a midsection via a first resilient member, and at a trailing edge via a second resilient member. As the aerial vehicle is in flight, it is subject to loads. The connections of the surfaces provides flexibility and resiliency to maintain the surfaces in communication with the fuselage and to allow regulated separation of the winged surfaces at their rear edges in a first direction in a first flexed state and at their front edges in a second direction, different from the first direction, in a second flexed state.
摘要翻译：实施例包括飞行器。提供与机身连通的两个翼状表面。这些表面经由袖带在前边缘处经由第一弹性构件在中间连接，并且在后缘处经由第二弹性构件连通。当飞行器在飞行中时，它将受到负载的影响。表面的连接提供了灵活性和弹性，以保持与机身连通的表面，并且允许翼形表面在其后边缘处以第一弯曲状态的第一方向和在其第二方向的前边缘处被调节分离，与第一方向不同，处于第二弯曲状态。

86. 发明申请

US20140003941A1 HYDRUALIC CONTROL VALVE, A DEVICE FOR ADJUSTING BLADE PITCH, AND AN AIRCRAFT PROVIDED WITH SUCH A HYDRAULIC CONTROL VAVLE 有权
标题翻译：液压控制阀，用于调整叶片的装置和具有这种液压控制装置的飞机
公开(公告)号：US20140003941A1
公开(公告)日：2014-01-02
申请号：US13911436
申请日：2013-06-06
申请人： EUROCOPTER
发明人： Maxime Leclercq , Bernard Gemmati , Philippe Veron , Francois Malburet
IPC分类号： B64C3/40
CPC分类号： B64C3/40 , B64C11/38 , B64C27/26 , F15B9/10 , Y10T137/8671
摘要： A hydraulic control valve (10) provided with at least one body (11) having a jacket (12) with a feed orifice (13). The hydraulic control valve (10) has a transfer rod (15) provided with at least one fluid transfer duct (16), at least one orifice (17) present inside the jacket (12), and a second orifice (18) arranged outside the jacket (12). The jacket (12) has a feed chamber (25) connected to said feed orifice (13) and a main fluid-return chamber (30) connected to discharge means (50) for discharging the fluid, control means (20) being secured to the jacket (12) in order to move the jacket (12) in translation relative to said transfer rod (15) so as to control the flow of fluid within said transfer rod (15).
摘要翻译：一个设置有至少一个主体（11）的液压控制阀（10），该主体具有带进料口（13）的护套（12）。液压控制阀（10）具有设置有至少一个流体传送管道（16）的传递杆（15），存在于护套（12）内的至少一个孔口（17）和布置在外部的第二孔口（18）夹克（12）。护套（12）具有连接到所述进料孔（13）的进料室（25）和连接到用于排放流体的排出装置（50）的主流体回流室（30），控制装置（20）被固定到护套（12），以相对于所述传送杆（15）移动所述护套（12）平移，以便控制所述传送杆（15）内的流体的流动。

87. 发明申请

US20050274844A1 PIVOTING AIRCRAFT WING AND ASSOCIATED METHOD 有权
标题翻译：起飞航空和相关方法
公开(公告)号：US20050274844A1
公开(公告)日：2005-12-15
申请号：US10864114
申请日：2004-06-09
申请人： Victor Stuhr
发明人： Victor Stuhr
IPC分类号： B64C3/38 , B64C3/40
CPC分类号： B64C3/40 , Y02T50/14
摘要： A pivoting aircraft wing and associated system and method are provided. The pivoting aircraft wing includes a wing member, a carry-through structure, and a spar box assembly pivotally connected to the carry-through structure. The spar box assembly extends longitudinally within the wing member. The spar box assembly comprises a spar box and a bearing support structure attached to the spar box. The aircraft wing further includes a plurality of bearings disposed within a plurality of bearing races defined by the bearing support structure and carry-through structure. The plurality of bearing races advantageously define an arcuate path of rotation such that the wing member is capable of rotating about a virtual axis of rotation.
摘要翻译：提供了一种枢转飞机机翼及相关系统和方法。枢转飞行器机翼包括翼构件，承载结构和枢转地连接到承载结构的翼梁箱组件。翼梁箱组件在机翼构件内纵向延伸。翼梁箱组件包括翼梁箱和连接到翼梁箱的轴承支撑结构。飞机机翼还包括设置在由轴承支撑结构和承载结构限定的多个轴承座内的多个轴承。多个轴承座有利地限定了弧形的旋转路径，使得翼构件能够围绕虚拟的旋转轴线旋转。

88. 发明授权

US5992796A Secondary wing system for use on an aircraft 失效
标题翻译：用于飞机的二次翼系统
公开(公告)号：US5992796A
公开(公告)日：1999-11-30
申请号：US828826
申请日：1997-03-13
申请人： Brian E. Smith
发明人： Brian E. Smith
IPC分类号： B64C1/26 , B64C3/40 , B64C5/02 , B64C5/04 , B64C5/12 , B64C5/14 , B64C30/00 , B64C39/12 , B64C3/56
CPC分类号： B64C30/00 , B64C1/26 , B64C3/40 , B64C39/12 , B64C5/02 , B64C5/04 , B64C5/12 , B64C5/14 , Y02T50/145
摘要： A secondary wing system for use on an aircraft augments the lift, stability, and control of the aircraft at subsonic speeds. The secondary wing system includes a mechanism that allows the canard to be retracted within the contour of the aircraft fuselage from an operational position to a stowed position. The top surface of the canard is exposed to air flow in the stowed position, and is contoured to integrate aerodynamically and smoothly within the contour of the fuselage when the canard is retracted for high speed flight. The bottom portion of the canard is substantially flat for rotation into a storage recess within the fuselage. The single canard rotates about a vertical axis at its spanwise midpoint. The canard can be positioned between a range of sweep angles during flight and a stowed position in which its span is substantially parallel to the aircraft fuselage. The canard can be deployed and retracted during flight. The deployment mechanism includes a circular mounting ring and drive mechanism that connects the canard with the fuselage and permits it to rotate and to change incidence. The deployment mechanism further includes retractable fairings which serve to streamline the wing when it is retracted into the top of the fuselage.
摘要翻译：在飞机上使用的二次翼系统以亚音速提升飞机的提升，稳定性和控制。副翼系统包括一种机构，其允许将卡车从飞行器机身的轮廓从操作位置缩回到收起位置。将鸭子的顶部表面暴露在收起位置的空气流中，并在轮廓缩回以进行高速飞行时，在机身轮廓内空气动力学和平滑地整合。该底部的底部基本上是平的，用于旋转进入机身内部的存储凹槽。单个鸭嘴在其横向中点处围绕垂直轴线旋转。该挡板可位于飞行期间的扫掠角范围和其跨度基本上平行于飞行器机身的收起位置之间。在飞行过程中，可以部署和收回鸭子。展开机构包括一个环形安装环和驱动机构，将机箱与机身连接，并允许其旋转并改变发生。展开机构还包括可伸缩整流罩，用于在机翼缩回到机身顶部时简化机翼。

89. 发明授权

US5312070A Segmented variable sweep wing aircraft 失效
标题翻译：分段可变扫掠翼飞机
公开(公告)号：US5312070A
公开(公告)日：1994-05-17
申请号：US862318
申请日：1992-04-02
申请人： Aldo Arena
发明人： Aldo Arena
IPC分类号： B64C3/40 , B64C9/28 , B64C3/38
CPC分类号： B64C3/40 , B64C9/28
摘要： A segmented variable sweep wing for an aircraft has a plurality of wing segments. A structural device movably affixes the wing segments to the fuselage of the aircraft adjacent each other at their root areas. The structural device moves the segments conjointly to a power position where the segments are perpendicular to the fuselage and spaced from each other. The structural device also moves the segments conjointly to a cruise position wherein the segments are swept back at an angle with the fuselage and in abutment with each other thereby forming a unitary continuous surface airfoil.
摘要翻译：用于飞机的分段可变扫掠翼具有多个翼段。结构装置将翼段可移动地固定在其根部区域相邻的飞行器的机身上。结构装置将片段联合地移动到其中片段垂直于机身并彼此间隔开的功率位置。结构装置还将段连续地移动到巡航位置，其中段与机身以一定角度扫掠并彼此邻接，从而形成整体连续的表面翼型。

90. 发明授权

US4243192A Ball pivot thrust bearing flex joint 失效
标题翻译：滚珠轴承止推轴承挠性接头
公开(公告)号：US4243192A
公开(公告)日：1981-01-06
申请号：US966337
申请日：1978-12-04
申请人： Robert E. Johnson
发明人： Robert E. Johnson
IPC分类号： B64C3/40 , B64C3/50 , B64C1/00
CPC分类号： B64C3/40 , Y10T403/32704 , Y10T403/32926
摘要： A ball pivot thrust bearing flex joint assembly having an inner race member and an outer race member, the inner surface of the outer race member being a concave spherical self lubricating surface which provides a maximum envelopment of the complementary convex spherical outer surface of the inner pivoting ball race. The inner race ball is provided with a through aperture along the axis of primary motion for acceptance of a through shaft or bolt, and is provided with integral lateral extensions which are necked down to provide clearance for secondary axis motion. The end portions of the through hole aperture are provided with self lubricating bearings which support the radial loads and accommodate main axis rotation. Flat, washer type, self lubricating bearings are provided between the ends of the inner race pivoting ball and the associated clevis. Thus high thrust loads are accommodated with limited secondary axis motion about the complementary spherical surfaces and primary motion is accommodated about the shaft or bolt center line radial bearings.
摘要翻译：一种具有内座圈构件和外圈构件的球轴承止推轴承挠性接头组件，外座圈构件的内表面是凹球形自润滑表面，其提供内枢转的互补凸球面外表面的最大包络球赛内座圈球沿着一次运动的轴线设置有通孔，用于接纳通轴或螺栓，并且设有一体的侧向延伸部，颈部向下缩小以提供副轴运动的间隙。通孔孔的端部设置有支承径向载荷并适应主轴旋转的自润滑轴承。平衡式，垫圈式，自润滑轴承设置在内圈枢转球和相关联的U形夹的端部之间。因此，在推力负载较大的情况下，围绕互补球形表面受到有限的次轴运动，主轴运动容纳在轴或螺栓中心线径向轴承周围。

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