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1. 发明申请

WO2016079743A1 SOLID-LIQUID COMPOSITE STRUCTURES 审中-公开
标题翻译：固体液体复合结构
公开(公告)号：WO2016079743A1
公开(公告)日：2016-05-26
申请号：PCT/IL2015/051117
申请日：2015-11-19
申请人： TECHNION RESEARCH & DEVELOPMENT FOUNDATION LIMITED
发明人： GAT, Amir , ELBAZ, Shai , MATIA, Yoav
IPC分类号： B64C3/36 , B64C13/36 , B64C9/06 , F01D5/16 , B25J18/06
CPC分类号： B64C3/185 , B29L2031/3085 , B64C1/34 , B64C3/38
摘要： A pressurized, fluid-filled channel network embedded in an elastic structure, asymmetrically to the neutral plane, is used to create a deformation field within the structure by the pressurization of the embedded fluidic network, which can be applied in accordance with external forces acting on the structure. The deformation of the structure resulting from the liquid pressure and geometry of the network is related to a continuous deformation-field function. This enables the design of networks creating steady arbitrary deformation fields as well as to eliminate deformation created by external time varying forces, thus increasing the effective rigidity of the beam. By including the effects of the deformation created by the channel network on the beam inertia, the response of the beam to oscillating forces can be modified, enabling the design of channel networks which create pre-defined oscillating deformation patterns in response to external oscillating forces.
摘要翻译：嵌入在弹性结构中的加压流体填充的通道网络不对称地用于通过嵌入式流体网络的加压在结构内产生变形场，该变形场可以根据作用在其上的外力施加结构。由液体压力和网络几何结构引起的结构变形与连续变形场函数有关。这使得网络的设计可以创建稳定的任意变形场，并且消除由外部时变力产生的变形，从而增加梁的有效刚度。通过包括由通道网络产生的变形对波束惯性的影响，可以修改波束对振荡力的响应，使得能够设计响应于外部振荡力产生预定的振荡变形模式的通道网络。

2. 发明申请

WO2014126855A1 SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 审中-公开
标题翻译：用于控制SONIC BOOM磁头的系统和方法
公开(公告)号：WO2014126855A1
公开(公告)日：2014-08-21
申请号：PCT/US2014/015585
申请日：2014-02-10
申请人： GULFSTREAM AEROSPACE CORPORATION , FREUND, Donald
发明人： FREUND, Donald
IPC分类号： B64C3/20
CPC分类号： B64C23/00 , B64C3/185 , B64C3/20 , B64C3/38 , B64C3/42 , B64C9/00 , B64C17/10 , B64C30/00 , B64D37/00 , Y02T50/14 , Y02T50/44
摘要： A method of controlling a magnitude of a sonic boom caused by off-design condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.
摘要翻译：控制由超音速飞行器在超音速下的非设计状态操作引起的声波爆震震级的方法包括但不限于在超音速和非设计状态下操作超音速飞行器的步骤。超音速飞机具有一对扫掠翼，其具有多个以一定角度定向的复合层，使得最大刚度的轴相对于该对扫掠翼的每个翼的后翼片不平行。该方法还包括但不限于在复合帘布层的脱离设计条件下以超音速速度降低由超音速飞行器操作引起的机翼扭转的步骤。该方法还包括但不限于通过减少机翼扭曲来最小化声音吊杆的大小。

3. 发明申请

WO2016035068A2 TILT WINGED MULTI ROTOR 审中-公开
标题翻译：倾斜多功能转子
公开(公告)号：WO2016035068A2
公开(公告)日：2016-03-10
申请号：PCT/IL2015/050874
申请日：2015-08-31
申请人： AMIT, Regev
发明人： AMIT, Regev
IPC分类号： B64C27/24
CPC分类号： B64C27/10 , B64C3/38 , B64C29/0008 , B64C39/02 , B64C39/024 , B64C2201/027
摘要： A multirotor aircraft (100) that comprises a chassis (200), three or more engines (300) and one or more free wings (400). Each free wing (400) is attached to said chassis by an axial connection (18) in such a way that enables to change the attack angle of the free wing relative to said chassis according to the direction of the flow of air over the free wing. The aircraft may be equipped with control surfaces or movement-limiting devices.
摘要翻译：一种多转子飞机（100），包括底盘（200），三个或更多个发动机（300）和一个或多个自由翼（400）。每个自由翼（400）通过轴向连接（18）以这样的方式附接到所述底盘，使得能够根据空气流过自由翼的方向改变自由翼相对于所述底盘的攻角。飞机可能配备控制面或移动限制装置。

4. 发明申请

WO2009134486A3 FRANGIBLE FASTENERS AND ASSOCIATED SYSTEMS AND METHODS 审中-公开
标题翻译：可靠的紧固件和相关系统和方法
公开(公告)号：WO2009134486A3
公开(公告)日：2009-12-30
申请号：PCT/US2009032720
申请日：2009-01-30
申请人： INSITU INC , DENNIS BRIAN D
发明人： DENNIS BRIAN D
IPC分类号： B64C1/00
CPC分类号： B64C3/38 , B64C23/069 , B64C39/024 , B64C2201/021 , B64C2201/104 , F16B31/021 , F16B41/002 , Y02T50/164 , Y10T29/49947
摘要： Frangible fasteners and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage portion, a wing portion, and a winglet carried by the wing portion. The aircraft can also include at least one frangible fastener coupling the winglet to the wing portion. The fastener is coupled to only partially release the winglet from the wing portion when a force on the winglet exceeds a threshold value.
摘要翻译：本文公开了易碎紧固件及相关系统和方法。在一个实施例中，例如，无人飞行器可以包括机身部分，翼部分和由翼部分承载的小翼。飞机还可以包括将小翼片连接到机翼部分的至少一个易碎紧固件。当小翼上的力超过阈值时，紧固件联接成仅从翼部分部分地释放小翼。

5. 发明申请

WO2008054503A2 AIRCRAFT WINGS HAVING HINGED VANES AND AIRCRAFT HAVING SAID WINGS 审中-公开
标题翻译：具有铰链的航空器和具有所述机翼的飞机
公开(公告)号：WO2008054503A2
公开(公告)日：2008-05-08
申请号：PCT/US2007/008894
申请日：2007-04-10
申请人： KRETCHMER, Moshe
发明人： KRETCHMER, Moshe
IPC分类号： B64C15/00
CPC分类号： B64C3/38 , B64C27/26 , B64C27/28 , Y02T50/14
摘要： Reconfigurable aircraft wings with at least one set of hinged upper and lower vanes and aircraft that are equipped with such wings are provided. When the aircraft are taking off or landing vertically, the hinged vanes are open in order to allow rotor thrust to go through the wings, thereby permitting main rotors to be located above the wings. When the aircraft reach certain airspeeds, the hinged vanes are closed in order to provide normal lift of a fixed wing. The aircraft thereby take advantages of the helicopter and the traditional airplane with a fixed wing.
摘要翻译：提供了具有至少一组铰接的上下叶片和配备有这种翼的飞机的可重构飞机机翼。当飞机垂直起飞或着陆时，铰接叶片打开，以允许转子推力穿过机翼，从而允许主转子位于机翼上方。当飞机达到一定的空速时，铰链叶片关闭，以便提供固定翼的正常升力。因此，该飞机利用直升机和具有固定翼的传统飞机的优势。

6. 发明申请

WO02037661A1 ELECTROSTATIC/PNEUMATIC ACTUATORS FOR ACTIVE SURFACES 审中-公开
标题翻译：用于活性表面的静电/气动执行器
公开(公告)号：WO02037661A1
公开(公告)日：2002-05-10
申请号：PCT/US2001/045473
申请日：2001-11-01
IPC分类号： B64C3/38 , B64C3/46 , B64C13/48 , B64C13/50 , B64C21/10 , B64C23/00 , B81B3/00 , B81B7/04 , F04B43/04 , F15B15/10 , F15C5/00 , F15D1/12 , F16K99/00 , H02N1/00 , B64C3/30 , F04B43/00 , F16K31/02
CPC分类号： H02N1/006 , B64C3/38 , B64C3/46 , B64C13/48 , B64C13/50 , B64C21/10 , B64C23/005 , B81B3/0054 , B81B2203/053 , F04B43/043 , F15B15/103 , F15C5/00 , F15D1/12 , F16K99/0001 , F16K99/0015 , F16K99/0028 , F16K99/0051 , F16K2099/0078 , Y02T50/166
摘要： An actuator device controlling the shape of a flexible surface having a quasi-continuum in a plurality of locations. The device includes a plurality of individual cells arranged in an array for contact with the flexible surface. The cells comprise a cell body having an upper film portion and a lower film portion and an open central portion. The upper film portion is in contact with the flexible surface. A post is mounted in the open central portion and fixedly attached to the upper film portion and the lower film portion, the post defining a vertical axis of movement. The upper and lower film portions have electrodes mounted thereon respectively, positioned on the face of the upper and lower film portions and facing each other. A central diaphragm has electrodes on its outer surfaces and an open central portion surrounding the post. A power supply operably connected to the electrodes for causing selective cooperative electrostatic activation between them to move the post along the vertical axis to cause the upper film portion to move that portion of the flexible surface in which the upper film portion is in contact. In a preferred embodiment, the cell body has a circular cross section so that the post moves vertically upward and downward to raise or lower the portion of the flexible surface in contact with the upper film portion upon application of electrostatic potential between the electrodes.
摘要翻译：控制在多个位置具有准连续体的柔性表面的形状的致动器装置。该装置包括布置成阵列中的与柔性表面接触的多个单独电池。电池包括具有上膜部分和下膜部分以及开放中心部分的电池体。上部薄膜部分与柔性表面接触。柱安装在打开的中心部分中并且固定地附接到上膜部分和下膜部分，柱体限定了垂直运动轴线。上下薄膜部分分别安装在上薄膜部分和下薄膜部分的表面上且彼此面对的电极。中央隔膜在其外表面上具有电极，围绕柱的开放的中心部分。电源，其可操作地连接到所述电极，用于使它们之间的选择性协作静电激活沿着所述垂直轴线移动所述柱，以使所述上部膜部分移动所述上部膜部分接触的所述柔性表面的该部分。在优选实施例中，电池体具有圆形横截面，使得柱在垂直上下移动以在施加电极之间的静电电位时上升或下降与上部膜部分接触的柔性表面的部分。

7. 发明申请

WO01019671A1 WEIGHT-SHIFT-CONTROLLED AIRPLANE 审中-公开
标题翻译：平衡控制的飞机
公开(公告)号：WO01019671A1
公开(公告)日：2001-03-22
申请号：PCT/CH2000/000332
申请日：2000-06-19
IPC分类号： B64C3/38 , B64C17/04
CPC分类号： B64C17/04 , B64C3/38
摘要： The invention relates to a weight-shift-controlled airplane that is characterized by a novel design of airplanes with closed passenger compartment and that combines the advantages of conventional aerodynamically controlled airplanes with those of weight-shift-controlled ultra-light airplanes. The inventive weight-shift-controlled airplane comprises a passenger compartment with a fitted propeller (4) as the pressure drive and a chassis (7), an airfoil (1) and an adjustable support system between the passenger compartment and the airfoil (1) which allows that the airfoil (1) is tilted, for controlling the airplane.
摘要翻译：所提出的平衡控制模式的特点是新颖的结构的飞机具有封闭客舱，并结合常规的空气动力学控制的飞机与平衡控制超轻的优点。平衡控制的模型由乘客室的与附螺旋桨（4），为乘客车厢和（1），其具有支撑表面的倾斜载体表面之间的驱动和底座（7），所述支撑表面（1）和可调节的支撑系统（1），用于确保了飞机的控制。

8. 发明申请

WO9505974A3 MULTI-PURPOSE AIRCRAFT 审中-公开
标题翻译：多用途飞机
公开(公告)号：WO9505974A3
公开(公告)日：1995-06-08
申请号：PCT/US9409474
申请日：1994-08-24
申请人： GEVERS DAVID E
发明人： GEVERS DAVID E
IPC分类号： B64C1/00 , B64C3/38 , B64C3/54 , B64C3/56 , B64C25/52 , B64C25/54 , B64C25/66 , B64C35/00 , B64C35/02 , B64D27/00 , B64D27/02 , B64D27/08 , B64D29/04 , B64D35/04 , B64D25/08
CPC分类号： B64D35/04 , B64C1/00 , B64C3/38 , B64C3/54 , B64C3/56 , B64C25/52 , B64C25/54 , B64C25/66 , B64C35/00 , B64C35/002 , B64C35/008 , B64C2001/0045 , B64D27/00 , B64D27/08 , B64D29/04 , Y02T50/12 , Y02T50/145 , Y02T50/44
摘要： Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) (24,25) with a belt drive system (84,99) for turning wing-situated propellers (8,9); compound landing gear integrating ski (29,114), pontoon and wheel (18,19,21) subcomponents; pivotal mounting armatures (6,7) for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure (14,15) featuring extendable wing panels (4,5) that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.
摘要翻译：披露了一些飞机的创新系统，以及包含它们的飞机。特征包括内置式发动机（24,25），带有用于转动机翼定位螺旋桨（8,9）的皮带传动系统（84,99）; 复合起落架整合滑雪（29,114），浮桥和轮（18,19,21）子部件; 用于起落架和/或螺旋桨的枢转安装衔铁（6,7），其提供多个可能的起落架和/或螺旋桨结构; 以及具有可延伸的翼板（4,5）的复合翼结构（14,15），其允许飞行器的机翼跨度在飞行中几乎翻倍。结合这种特征的飞机将比常规多引擎飞机享有几个安全优势，并且能够在飞行期间进行修改，这些飞行器可以在雪，硬表面（跑道）和水中任何一个上升降。

9. 发明申请

WO2018186907A1 FLIGHT VEHICLE WING POSITIONING SYSTEM 审中-公开
公开(公告)号：WO2018186907A1
公开(公告)日：2018-10-11
申请号：PCT/US2017/056309
申请日：2017-10-12
申请人： RAYTHEON COMPANY
发明人： KOESSLER, Jeffrey, H. , LEE, Anthony, O. , TRETSCHOK, Cody, D. , ARTZ, Gregory, J.
IPC分类号： B64C3/38 , B64C17/00 , B64C39/00 , B64C39/02
CPC分类号： B64C3/38 , B64C1/22 , B64C1/26 , B64C17/02 , B64C39/008 , B64C39/024 , B64C2201/021 , B64C2201/10 , B64C2201/128 , B64C2201/165 , B64C2211/00
摘要： A control system of a flight vehicle automatically varies the relationship between the center of gravity and the center of pressure of the flight vehicle. The control system automatically adjusts a center of pressure of the flight vehicle depending on a varying payload or payload type that is removably couplable to the flight vehicle. The control system automatically limits translational movement of the one or more wings of the flight vehicle in response to coupling of a payload to a fuselage of the flight vehicle.

10. 发明申请

WO2018131821A1 받음각 자동 조절 날개 및 받음각 자동 조절 날개를 포함하는 항공기 및 선박 审中-公开
公开(公告)号：WO2018131821A1
公开(公告)日：2018-07-19
申请号：PCT/KR2017/015135
申请日：2017-12-20
申请人： 한국항공우주연구원
发明人： 최익현
IPC分类号： B64C3/38 , B64C27/59 , B63H3/00 , F03D7/02
CPC分类号： B63H3/00 , B64C3/38 , B64C27/59 , F03D7/02 , Y02E10/723
摘要： 본 발명은, 유체 흐름 방향의 변화에 따라 날개의 받음각이 자동으로 조절되어 항상 최적의 효율을 갖는 기준 받음각 상태를 유지하는 받음각 자동 조절 날개를 제공하는 것이며, 날개의 하방쪽 특정 지점에 날개 회전의 기준이 되는 받음각 조절축을 구비하고, 유체 흐름 방향의 변화에 의하여 날개의 받음각이 기준 받음각에서 달라졌을 때, 날개가 상기 받음각 조절축을 중심으로 자동으로 회전하여 기준 받음각으로 자동으로 복귀하는 것이다. 본 발명은 위 구성으로 인해 날개의 받음각을 항상 최적 효율의 상태로 유지할 수 있기 때문에 공기력 활용의 효과가 매우 증대되고, 날개 또는 프로펠러를 이용하여 양력 또는 추력을 발생시켜서 작동하는 모든 장치에 적용이 가능하며 이들 장치의 효율이 상승되는 효과를 발휘한다.

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