公开(公告)号：US20150102157A1

公开(公告)日：2015-04-16

申请号：US14460013

申请日：2014-08-14

Applicant: SWIFT ENGINEERING, INC.

Inventor： Robert Godlasky ,  Nate Ogawa ,  Andrew Streett

IPC: B64C29/00 ,  B64C3/56 ,  B64D27/02

CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

Abstract translation: 垂直起落飞行器包括至少一个牵引转子和至少一个推动器转子。 例如，VTOL飞机可以包括三个牵引转子和一个推动器转子。 静态牵引器和推动器转子的组合允许转子相对于垂直起降飞机的机翼和机身保持在固定方向（即，不需要移动的机械轴），同时能够使飞机从基本垂直的飞行 到达基本水平的飞行路径的路径。

公开(公告)号：US09004393B2

公开(公告)日：2015-04-14

申请号：US13279827

申请日：2011-10-24

Applicant: Ronald M. Barrett-Gonzales

Inventor： Ronald M. Barrett-Gonzales

IPC: B64C27/24 ,  B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C27/24 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/084 ,  B64C2201/102

Abstract: Embodiments of the present invention include an aircraft capable of sustained out-of-ground-effect hover flight and sustained supersonic flight. At least some embodiments includes two wings powered by an engine to counterrotate while hovering, and to not rotate and sweep while flying at transonic and supersonic speeds. Other embodiments include two rotating wings that generate a force per unit area of under 100 lb/ft2 within the rotating wing disk during hover. Still other embodiment include a vehicle with rotating wings that can increase pitch to accelerate the aircraft, align the chord line of the wings with the airstream, and sweep the wings. Still further embodiments include a power plant that powers unducted rotating wings during hover and disengages from the wings to propel the aircraft at supersonic speeds.

Abstract translation: 本发明的实施例包括能够持续地面效应悬停飞行和持续的超音速飞行的飞机。 至少一些实施例包括由发动机驱动的两个翼，以在盘旋时反向旋转，并且在以跨音速和超音速飞行的同时不旋转和扫掠。 其它实施例包括两个旋转翼，其在悬停期间在旋转翼盘内产生每100英寸/ ft 2以下的每单位面积的力。 另外的实施例包括具有旋转翼的车辆，其可以增加俯仰以加速飞行器，将翼的弦线与气流对准，并且扫掠翼。 另外的实施例包括在悬停期间为未被引导的旋转翼提供动力的动力装置，并且与翼分离，以超音速推进飞行器。

公开(公告)号：US08894007B2

公开(公告)日：2014-11-25

申请号：US13558728

申请日：2012-07-26

Applicant: Andrew McComas ,  Jon Clark

Inventor： Andrew McComas ,  Jon Clark

IPC: B64F1/04 ,  B64F1/06

CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/102

Abstract: A canister system for a folding aircraft may include a canister housing and a launch mechanism powered by one or more compression springs. A hand-operated drive mechanism may rotate a plurality of threaded rods to drive the launch mechanism from a released position to a cocked position, in which mechanical energy is stored in the springs. A latch mechanism may capture the launch mechanism in the cocked position. The canister may include a housing for receiving and storing the aircraft when the launch mechanism is in the cocked position. A trigger mechanism may release the latch mechanism, permitting the energy stored in the compressed springs to drive the launch mechanism toward the released position and propel the aircraft from the housing at launch velocity.

Abstract translation: 用于折叠飞机的罐系统可以包括罐壳体和由一个或多个压缩弹簧驱动的发射机构。 手动驱动机构可以旋转多个螺杆，以将发射机构从释放位置驱动到起动位置，其中机械能存储在弹簧中。 闩锁机构可以捕捉发动机构处于俯视位置。 罐可以包括用于在发射机构处于起动位置时接收和存储飞行器的壳体。 触发机构可以释放闩锁机构，允许存储在压缩弹簧中的能量将发射机构驱动到释放位置，并以发射速度将飞行器从壳体推进。

公开(公告)号：US08783604B2

公开(公告)日：2014-07-22

申请号：US13278477

申请日：2011-10-21

Applicant: Terry M. Sanderson ,  Michael S. Cherry ,  Jack W. Reany

Inventor： Terry M. Sanderson ,  Michael S. Cherry ,  Jack W. Reany

IPC: B64C3/56

CPC classification number: B64C3/56 ,  B64C2201/102

Abstract: An aircraft wing has hinged ribs, and a skin covering the ribs. The ribs each include plural rib sections, array from the leading edge of the wing, to the trailing edge of the wing, and a lock to hold the rib sections together in a deployed state or condition. The wings are initially in a stowed state, with the ribs and the rib sections having a curved chord, and deploy to the deployed state, in which the ribs have a straightened chord that defines an airfoil state. The wing may have foam material between the ribs to allow the wings to expand in the wingspan direction, for instance after the ribs have been placed in the deployed state.

Abstract translation: 飞机机翼有铰链肋骨和覆盖肋骨的皮肤。 肋条各自包括从翼的前缘到翼的后缘阵列的多个肋部，以及在展开状态或状态下将肋部保持在一起的锁。 翼部最初处于收起状态，肋和肋部具有弯曲的弦，并且部署到展开状态，其中肋具有限定翼型状态的矫直弦。 机翼可以在肋之间具有泡沫材料，以允许翼在翼展方向上膨胀，例如在肋已经处于展开状态之后。

公开(公告)号：US08727280B1

公开(公告)日：2014-05-20

申请号：US12633272

申请日：2009-12-08

Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C1/00 ,  B64C3/00 ,  B64C5/00

CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

Abstract translation: 一种用于操作翼型系统的方法和装置。 可能产生气体。 气体可以被送入包括可膨胀的气翼和截面的充气翼型系统中。 可膨胀翼型件可以具有内端和外端，其中可膨胀翼型可以由许多基本上通过电磁波通过可充气翼型的材料构成。 该部分可以具有多个开口，其中可充气翼片的内端可以与该部分相关联。 该部分可以被配置为与机身相关联。 开口的数量可以被配置为提供与可膨胀翼型件的内部的通信。 具有开口数量的部分可以被配置为减少遇到该部分的电磁波的反射。

公开(公告)号：US20140091172A1

公开(公告)日：2014-04-03

申请号：US13899252

申请日：2013-05-21

Applicant: Paul E. Arlton ,  David J. Arlton

Inventor： Paul E. Arlton ,  David J. Arlton

IPC: B64C27/10

CPC classification number: B64C27/605 ,  B64C7/00 ,  B64C27/10 ,  B64C27/14 ,  B64C39/024 ,  B64C2027/8236 ,  B64C2027/8281 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract translation: 旋转翼车辆包括具有细长管状骨架或芯体的主体结构，以及具有转子的反向旋转同轴转子系统，每个转子具有单独的电动机，以围绕公共转子旋转轴线驱动转子。 转子系统用于在定向飞行中移动旋翼机。

公开(公告)号：US20130306789A1

公开(公告)日：2013-11-21

申请号：US13475371

申请日：2012-05-18

Applicant: Suneal Guptaa ,  Jeremy Bley

Inventor： Suneal Guptaa ,  Jeremy Bley

IPC: B64C3/56 ,  B65B43/00 ,  B65D6/00 ,  B65B11/00

CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/102 ,  F42B10/16 ,  Y02T50/14

Abstract: An air vehicle, as well as a method for folding an air vehicle for storage, may include a fuselage and a wing connected to the fuselage. The wing may include two ends positioned opposite from each other, and the wing may be substantially perpendicular to the fuselage. At least one of the ends may define a space therebetween the fuselage and the wing. The space may be sized to receive a potion of the wing when the wing is wrapped around the fuselage.

Abstract translation: 一种空中飞行器以及用于折叠用于存储的空中飞行器的方法可以包括机身和连接到机身的机翼。 机翼可以包括彼此相对定位的两个端部，并且机翼可以基本上垂直于机身。 端部中的至少一个可以限定机身和机翼之间的空间。 当机翼围绕机身缠绕时，该空间的大小可以接收机翼的一部分。

公开(公告)号：US08528863B2

公开(公告)日：2013-09-10

申请号：US12463400

申请日：2009-05-10

Applicant: Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

Inventor： Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

IPC: B64C3/20 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  F42B10/14 ,  F42B10/146 ,  F42B10/16 ,  F42B10/20

Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

Abstract translation: 层压翼结构包括至少一层金属材料和至少一层形状记忆聚合物（SMP）材料。 将SMP加热到其玻璃化转变带Tg的温度，以将机身周围的机翼卷绕成储存位置。 金属层必须足够薄以便在卷起时保持低于其屈服点。 在准备发射时，SMP材料被热激活，允许存储在金属材料层中的应变能在发射时将机翼返回到其展开位置。 一旦部署，SMP冷却到玻璃状态。 SMP材料可以用纤维增强以形成聚合物基质复合材料（PMC）。 SMP可用于为多个金属层提供剪切应变消除。 通过卸载将机翼从SMP返回到金属的原始展开位置所需的动力，聚合物不会获得永久变形，并且可以准确地展开机翼。

公开(公告)号：US08469307B2

公开(公告)日：2013-06-25

申请号：US13270872

申请日：2011-10-11

Applicant: Paul E Arlton ,  David J Arlton

Inventor： Paul E Arlton ,  David J Arlton

IPC: B64C27/10 ,  B64C27/54 ,  B64C27/58

CPC classification number: B64C27/10 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract translation: 旋转翼车辆包括具有细长管状骨架或芯体的主体结构，以及具有转子的反向旋转同轴转子系统，每个转子具有单独的电动机，以围绕公共转子旋转轴线驱动转子。 转子系统用于在定向飞行中移动旋翼机。

公开(公告)号：US20130146716A1

公开(公告)日：2013-06-13

申请号：US13324193

申请日：2011-12-13

Applicant: Jonathan David Gettinger

Inventor： Jonathan David Gettinger

IPC: B64C3/56 ,  B64C3/50

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C5/12 ,  B64C2201/102

Abstract: Deployment and control actuation mechanisms are incorporated in unmanned aerial vehicles having folding wings and/or folding canards and/or a folding vertical stabilizer. The folding canards and folding vertical stabilizer can be deployed using respective four-bar over-center mechanisms. Elevators pivotably mounted to the folding canards and a rudder pivotably mounted to the folding vertical stabilizer can be controlled by means of respective twist link mechanisms. The folding wings have respective wing roots that are driven by respective gas springs to pivot on bearings about a wing root hub having control servo wire paths.

Abstract translation: 部署和控制致动机构被并入具有折叠翼和/或折叠的猫和/或折叠的垂直稳定器的无人驾驶飞行器中。 可以使用相应的四杆过中心机构来部署折叠式鸭子和折叠式垂直稳定器。 可枢转地安装到折叠卡瓦的电梯和可枢转地安装到折叠垂直稳定器的舵可以通过相应的扭转连杆机构来控制。 折叠翼具有相应的翼根，其由相应的气弹簧驱动，以围绕具有控制伺服线路径的翼根轮毂的轴承枢转。