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1. 发明公开

EP3409581A1 WING FOLD CONTROLLER 有权转让
公开(公告)号：EP3409581A1
公开(公告)日：2018-12-05
申请号：EP18184756.7
申请日：2013-10-24
申请人： The Boeing Company
发明人： LASSEN, Matthew August , DOUGLAS, Chad Richard , JONES, Kelly Thomas , KENNING, Terence Boyd
IPC分类号： B64C3/56 , B64C23/06
CPC分类号： B64C3/56 , B64C23/072 , Y02T50/14 , Y02T50/164 , Y02T50/54
摘要： Illustrative embodiments may provide for an apparatus and method of controlling the folding of a wing. The apparatus may include a sensor, an actuator, and a wing fold controller. The method may include receiving a status of at least one of an aircraft and a wing fold system of the aircraft by the wing fold controller of the wing fold system. The method may also include receiving an automated command by the wing fold controller in response to receiving the status. The method may also include operating the wing fold system by the wing fold controller based on the automated command and the status. The method may also include transitioning a wingtip of a wing of the aircraft to one of a flight position and a folded position by an actuator of the wing fold system in response to commands from the wing fold controller.

2. 发明公开

EP3402718A1 HYBRID PROPULSION VERTICAL TAKE-OFF AND LANDING AIRCRAFT 有权
公开(公告)号：EP3402718A1
公开(公告)日：2018-11-21
申请号：EP17701961.9
申请日：2017-01-12
申请人： Aurora Flight Sciences Corporation
发明人： GIANNINI, Francesco , GOMEZ, Martin , COTTRELL, Dan , LEDE, Jean-Charles , ROBERTS, Tom , SCHAEFER, Carl, Jr. , COLAS, Dorian , WHIPPLE, Brian , NUHFER, Tim , HUNTER, Herb , GROHS, Jonathon , PETULLO, Steve
IPC分类号： B64C3/38 , B64C5/04 , B64C5/16 , B64C29/00 , B64C39/12 , B64D27/02 , B64D27/24
CPC分类号： B64C29/0033 , B64C3/385 , B64C5/04 , B64C5/16 , B64C39/024 , B64C39/12 , B64C2201/021 , B64C2201/042 , B64C2201/048 , B64D27/24 , B64D29/02 , B64D2027/026 , Y02T50/14 , Y02T50/44 , Y02T50/64
摘要： A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

3. 发明公开

EP3309062A1 SYSTEM AND METHOD FOR CORRECTING WING TWIST OF AN AIRCRAFT 有权转让
标题翻译：用于校正飞机的翼旋转的系统和方法
公开(公告)号：EP3309062A1
公开(公告)日：2018-04-18
申请号：EP17195884.6
申请日：2017-10-11
申请人： The Boeing Company
发明人： PROVOST, Stephen N. , PITT, Dale M.
IPC分类号： B64C13/16 , B64D45/00 , B64C3/38
CPC分类号： B64C13/16 , B64C3/385 , B64D43/00 , B64D45/00 , G01B11/16 , Y02T50/14
摘要： A system which includes a first light beam locating sensor associated with a first position to be located on a wing of an aircraft. The first light beam locating sensor senses a first light beam at an identifiable position on the first light beam locating sensor. A processor is configured to receive a first signal from the first light beam locating sensor wherein the first signal includes a first identifiable position on the first light beam locating sensor. The processor is configured to determine a location of the first position on the wing and perform a first comparison of the location of the first position on the wing to a predetermined analyzed location of the first position on the wing.
摘要翻译：一种系统，其包括与位于飞机机翼上的第一位置相关联的第一光束定位传感器。第一光束定位传感器在第一光束定位传感器上的可识别位置处感测第一光束。处理器被配置为从第一光束定位传感器接收第一信号，其中第一信号包括第一光束定位传感器上的第一可识别位置。处理器被配置成确定机翼上的第一位置的位置并且执行机翼上的第一位置的位置与机翼上的第一位置的预定分析位置的第一比较。

4. 发明公开

EP3301015A1 MORPHING WING FOR AN AIRCRAFT 审中-公开
标题翻译：变形翼为飞机
公开(公告)号：EP3301015A1
公开(公告)日：2018-04-04
申请号：EP17194415.0
申请日：2013-06-21
申请人： Bombardier Inc. , Learjet Inc.
发明人： XI, Fengfeng , FINISTAURI, Allan Daniel , MOOSAVIAN, Amin
IPC分类号： B64C3/44 , B64C3/52
CPC分类号： B64C3/38 , B64C3/385 , B64C3/40 , B64C3/44 , B64C3/52 , B64C3/54 , B64C2003/445 , B64C2003/543 , Y02T50/14
摘要： A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration.
摘要翻译：飞机的变形机翼包括顶面，底面，前缘，后缘，尖端和根部。多个结构肋设置在根部和尖端之间，使得它们在顶部表面和底部表面之间延伸并且与其横向轴线相交。至少一个活动构件沿着或者相对于横向轴线以第一角度连接在两个相邻的结构肋之间。活动构件可主动调整。至少一个被动构件沿着或者相对于横向轴线以第二角度连接在两个相邻结构肋之间。被动部件被动调节。至少一个主动构件的调节使相邻的结构肋相对于彼此移动，由此使机翼从第一构型变形为第二构型。

5. 发明公开

EP3281866A2 A ROTATIONAL JOINT FOR AN AIRCRAFT FOLDING WING 有权
标题翻译：飞机折叠翼的旋转接头
公开(公告)号：EP3281866A2
公开(公告)日：2018-02-14
申请号：EP17175292.6
申请日：2017-06-09
申请人： Airbus Operations Limited , Airbus Operations GmbH
发明人： BISHOP, Benjamin , WINKELMANN, Christoph , RUPP, Johannes
IPC分类号： B64C23/06
CPC分类号： B64C3/56 , B64C23/072 , F16C11/10 , Y02T50/14 , Y02T50/164
摘要： An aircraft (2) comprising a wing (1) which comprises a fixed wing (3) and a wing tip device (4) that is rotatable between a flight configuration and a ground configuration, the aircraft having a rotational joint (10) rotatably coupling the wing tip device to the fixed wing (3) and a locking mechanism (46) for locking the rotation mechanism (11) such that the wing tip device is locked in the flight and ground configurations. The locking mechanism (11) comprises first and second locking members (51, 52) and first and second receiving members (53, 54), the locking mechanism (46) locking the wing tip device in a flight configuration or ground configuration by receiving the locking members in the receiving members respectively, and to lock the wing tip device (4) in the other of the flight configuration and ground configuration by receiving the first locking member (51) in the second receiving member (54).
摘要翻译：一种包括机翼（1）的飞机（2），所述机翼包括固定翼（3）和可在飞行构型和地面构型之间转动的翼尖装置（4），所述飞机具有可旋转地联接（3）的翼尖装置和用于锁定旋转机构（11）的锁定机构（46），使得翼尖装置锁定在飞行和地面构型中。所述锁定机构（11）包括第一和第二锁定构件（51,52）以及第一和第二接收构件（53,54），所述锁定机构（46）通过将所述翼尖装置锁定在飞行构型或地面构型中锁定构件，并且通过将第一锁定构件（51）容纳在第二容纳构件（54）中来将翼尖装置（4）锁定在飞行构型和地面构型中的另一个中。

6. 发明公开

EP3261924A1 SOLAR POWERED AIRCRAFT WITH A VARIABLE GEOMETRY WING AND TELECOMMUNICATIONS NETWORKS UTILIZING SUCH AIRCRAFT 审中-公开
标题翻译：使用此类飞机的具有可变几何翼和电信网络的太阳能动力飞机
公开(公告)号：EP3261924A1
公开(公告)日：2018-01-03
申请号：EP16756283.4
申请日：2016-02-24
申请人： Karem Aircraft, Inc.
发明人： KAREM, Abe , TIGNER, Benjamin
IPC分类号： B64C39/02 , B64C3/38 , B64D27/24 , B64D41/00 , B64C11/28 , B64C13/50 , B64C25/10 , B64D45/00 , H04B7/185 , H02S10/40
CPC分类号： B64C3/52 , B64C3/24 , B64C3/42 , B64C3/546 , B64C11/30 , B64C13/00 , B64C25/10 , B64C39/02 , B64C39/024 , B64C39/04 , B64C39/10 , B64C2201/021 , B64C2201/042 , B64C2201/102 , B64C2201/122 , B64C2201/165 , B64D27/24 , H02S20/30 , H04B7/18506 , Y02T50/14 , Y02T50/44 , Y02T50/62
摘要： A solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network. A telecommunications network incorporating such aircraft is also discussed.

7. 发明公开

EP3254954A1 FOLDABLE WING AND ACTUATING ARRANGEMENT 有权
标题翻译：可折叠翼和促动安排
公开(公告)号：EP3254954A1
公开(公告)日：2017-12-13
申请号：EP16173832.3
申请日：2016-06-09
申请人： Airbus Operations GmbH , Airbus Operations Limited
发明人： Winkelmann, Christoph , Rupp, Johannes , Brakes, David
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , F15B15/02 , F15B2015/206 , F16H19/08 , F16H48/20 , Y02T50/14
摘要： A wing arrangement for an aircraft is described comprising a wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled with each other so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19'), and an actuating arrangement having an actuator (21) which is coupled to the base section (7) and the tip section (13) and which is operable to effect a pivotal movement of the tip section (13) relative to the base section (7) between a stowed position and a deployed position, wherein the actuator (21) has a rotatable actuator input shaft (37), a differential gearbox (61) having a rotatable output shaft (63), a first rotatable input shaft (65) and a second rotatable input shaft (67), wherein the first input shaft (65) of the differential gearbox (61) is coupled to the output shaft of the first motor (69) and the second input shaft (67) of the differential gearbox (61) is coupled to the output shaft of the second motor (73) and wherein the output shaft (63) of the differential gearbox (61) is coupled to the actuator input shaft (37).
摘要翻译：描述了用于飞行器的机翼装置，其包括具有底座部分（5）和顶端部分（13）的机翼（5），底座部分（7）具有第一端部分（9）和第二端部分（11 ），所述末端部分（13）具有第三端部（15）和第四末端部分（17），其中所述第二末端部分（11）和所述第三末端部分（15）彼此耦合，使得所述末端部分（13）能够围绕枢转轴线（19,19'）相对于所述基部（7）枢转，以及具有致动器（21）的致动装置，所述致动器联接到所述基部部分（7），并且所述末端部分（13）并且可操作以实现所述尖端部分（13）相对于所述基部（7）在收起位置和展开位置之间的枢转运动，其中所述致动器（21）具有可旋转致动器输入轴（37 ），具有可旋转输出轴（63），第一可旋转输入轴（65）和第二可旋转输入轴（67）的差速齿轮箱（61），其中第一输入轴差动齿轮箱61的输出轴65联接到第一马达69的输出轴上并且差动齿轮箱61的第二输入轴67联接到第二马达的输出轴上，（73），并且其中差速齿轮箱（61）的输出轴（63）联接到致动器输入轴（37）。

8. 发明公开

EP3190044A1 SYSTEM FOR LATCHING AND LOCKING A FOLDING WING 有权
标题翻译：锁紧折叠翼的系统
公开(公告)号：EP3190044A1
公开(公告)日：2017-07-12
申请号：EP17157513.7
申请日：2014-11-12
申请人： The Boeing Company
发明人： GOOD, Mark S. , WALKER, Steven Paul , LASSEN, Matthew A. , PIETERSEN, Quentin T.
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , Y02T50/14 , Y10T403/32254
摘要： A folding wing comprises a fixed section, a folding section, and a latch system for latching the folding section to the fixed section. The latch system includes a plurality of latch pins, and a corresponding plurality of non-backdriveable mechanical actuators for extending the latch pins to engage the folding section.
摘要翻译：折叠翼包括固定部分，折叠部分和用于将折叠部分锁定到固定部分的闩锁系统。闩锁系统包括多个闩锁销以及用于延伸闩锁销以接合折叠部的对应的多个非反向机械致动器。

9. 发明公开

EP2439138A3 Fluggerät mit variabler Geometrie 有权转让
标题翻译：可变几何的飞机
公开(公告)号：EP2439138A3
公开(公告)日：2017-07-12
申请号：EP11008130.4
申请日：2011-10-07
申请人： Airbus Defence and Space GmbH
发明人： Seifert, Jost, Dr.
IPC分类号： B64C3/42 , B64C39/06 , B64C3/16 , B64C3/10 , B64C3/56 , B64C3/54
CPC分类号： B64C3/42 , B64C3/10 , B64C3/16 , B64C3/546 , B64C3/56 , B64C39/068 , Y02T50/12 , Y02T50/14
摘要： Die Erfindung betrifft ein Fluggerät (10) mit variabler Geometrie zur Anpassung des Flugverhaltens an verschiedene Flugsituationen, umfassend einen Rumpf (12) mit einem Paar von beiderseits in Querrichtung (y) davon abstehenden Tragflügeln (14), die jeweils einen stationär bezüglich des Rumpfes (12) angeordneten inneren Tragflügelabschnitt (16) und einen sich daran anschließenden, um eine Schwenkachse (18) verschwenkbaren äußeren Tragflügelabschnitt (20) aufweisen. Derartige aus dem Stand der Technik als "Schwenkflügler" bekannte Fluggeräte besitzen eine Reihe von Nachteilen. Mit der Erfindung wird ein alternatives Konzept vorgeschlagen, bei welchem die Schwenkachse (18) in einer Richtung orientiert ist, die um maximal 40° von der Längsrichtung (x) des Fluggerätes (10) abweicht, also z. B. im Wesentlichen in dieser Längsrichtung (x) orientiert ist. Damit kann vorteilhaft z. B. ein "aerodynamischer Verschwenkungsantrieb" realisiert werden und/oder ein Zielkonflikt zwischen radarsignaturarmer Fluggerätform und Ermöglichung sowohl eines energieeffizienten Reisefluges als auch eines agilen Flugverhaltens entschärft werden.
摘要翻译：本发明涉及一种飞行器（10）具有可变的几何形状与在横向方向（y）的一对两侧的调整的浮动特性，以不同的飞行的情况下，其包括主体（12），其突出的翼部（14），其（在每种情况下的相对于所述船体静止 12）布置在内部机翼部分（16）和相邻的围绕枢转轴线（18）的可枢转外部机翼部分（20）。从现有技术已知的“摆翼”飞机具有许多缺点。通过本发明，另一种方法提出，其中所述枢转轴线（18），在该偏离由最大为40°与纵向方向（x）的飞机（10）的，即Z A方向定向。 B.基本上在该纵向（x）上取向。这可能是有利的z。例如，是一个“气动Verschwenkungsantrieb”被实现和/或飞行器的低雷达信号之间的折衷和形状使得两者的能量高效巡航飞行以及敏捷飞机行为来缓解。

10. 发明授权

EP2759469B1 Adaptive solar airframe 有权转让
标题翻译：适应性太阳能机身
公开(公告)号：EP2759469B1
公开(公告)日：2017-06-21
申请号：EP14152285.4
申请日：2014-01-23
申请人： Sunlight Photonics Inc.
发明人： Moussouris, John Peter , Frolov, Sergey V. , Cyrus, Michael
IPC分类号： B64C1/34 , B64C3/46 , B64C39/02 , B64D27/24 , G01S3/786
CPC分类号： B64C1/0009 , B64C1/34 , B64C3/46 , B64C39/024 , B64C2201/105 , B64D2211/00 , G01S3/7861 , Y02T50/14
摘要： Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes a solar PV system having at least one solar tracking system and being able to follow the sun position in order to increase sunlight collection and power output; and an expandable body having an aerodynamic cross-section that minimizes parasitic air drag at any given thickness of the body, further being at least partially transparent to sunlight, further enclosing the solar PV system, and further being able to change its shape in response to changes in the positions of the solar PV system.
摘要翻译：本文提供了用于可适应的太阳能机身的方法和设备。在一些实施例中，可适应的太阳能机身包括太阳能PV系统，其具有至少一个太阳能跟踪系统并且能够跟随太阳位置以增加太阳光收集和功率输出; 以及具有空气动力学横截面的可膨胀体，其使得在任何给定的身体厚度下的寄生空气阻力最小化，进一步对太阳光至少部分透明，进一步包围太阳能PV系统，并且还能够响应于太阳能光伏系统位置的变化。

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