公开(公告)号：US08393576B2

公开(公告)日：2013-03-12

申请号：US13445708

申请日：2012-04-12

Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C3/00

CPC classification number: B64C1/34 ,  B64C3/385 ,  B64C13/28 ,  B64C2201/105 ,  Y02T50/14

Abstract: An apparatus may comprise an inflatable control surface for an aircraft and an end of the inflatable control surface configured for attachment to a fuselage of the aircraft. The end of the inflatable control surface may be configured to be rotated about an axis to control movement of the aircraft during flight.

Abstract translation: 装置可以包括用于飞行器的可充气控制表面和构造成附接到飞行器的机身的可充气控制表面的一端。 可充气控制表面的端部可以被构造为绕轴线旋转以控制飞行器在飞行过程中的运动。

公开(公告)号：US20110174931A1

公开(公告)日：2011-07-21

申请号：US12656154

申请日：2010-01-19

Applicant: Jean C. Berland

Inventor： Jean C. Berland

IPC: B64D17/00

CPC classification number: B64D17/025 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/145 ,  B64D1/08

Abstract: An AGU adapted for one-time use is provided for use with a parachute. The AGU has a frame made of wood, plywood or other biodegradable material to which the parachute suspension lines are secured. The frame includes an exterior wall having an access portal to a compartment within which an avionics unit is mounted so that one side of the avionics unit remains exposed and substantially flush with the exterior wall. The avionics unit is secured to the frame around the perimeter of the access portal using connecting elements that can be removed by accessing only the exterior wall of the frame so that the avionics unit can be easily removed following deployment. The AGU also includes a harness that is wrapped around at least a part of the AGU frame and which provides multiple attachment points for securing of the AGU to the parachute suspension lines as well as to a payload, eliminating the need for any harness structural attachment points on the AGU frame.

Abstract translation: 适用于一次性使用的AGU提供与降落伞一起使用。 AGU具有由木材，胶合板或其他生物可降解材料制成的框架，降落伞悬挂线固定在该框架上。 框架包括外壁，其具有到隔室的通路入口，在该隔间内安装有航空电子单元，使得航空电子设备的一侧保持暴露并与外壁基本齐平。 使用连接元件将航空电子单元固定在接近门槛周边的框架上，连接元件只能通过仅访问框架的外壁来移除，以便在部署后可以方便地拆下航空电子设备。 AGU还包括缠绕在AGU框架的至少一部分上的线束，并且其提供用于将AGU固定到降落伞悬挂线以及有效载荷的多个附接点，从而不需要任何线束结构附接点 在AGU框架上。

公开(公告)号：US20100282897A1

公开(公告)日：2010-11-11

申请号：US11464973

申请日：2006-08-16

Applicant: Samuel de la Torre

Inventor： Samuel de la Torre

IPC: B64C3/56 ,  B64C3/00 ,  G01C21/00 ,  F42B25/00 ,  H04N7/18

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/203

Abstract: An aerial surveillance device is provided, comprising an image capturing device capable of being supported by an airframe structure above the ground. The airframe structure includes a body portion defining a longitudinal axis and configured to support the image-capturing device. A tail portion having control surfaces is operably engaged with the body portion along the axis. Transversely-extending wing portions are directly engaged with the body portion. Each wing portion is defined by longitudinally-opposed spars extending from a spaced-apart disposition at the body portion to a common connection distally from the body portion. The spars have a fabric extending therebetween to provide a wing surface. A support member extends along an aerodynamic center, transversely to the body portion, of each wing portion, to tension and rigidify the wing portions so as to provide a positive camber for the wing portions and to form an airfoil.

Abstract translation: 提供了一种空中监视装置，包括能够由地面上方的机身结构支撑的图像捕获装置。 机身结构包括限定纵向轴线并被配置为支撑图像捕获装置的主体部分。 具有控制表面的尾部部分沿着轴线与主体部分可操作地接合。 横向延伸的翼部直接与主体部分接合。 每个翼部分由纵向相对的翼梁限定，纵向相对的翼梁从主体部分处的间隔设置延伸到远离主体部分的公共连接。 翼梁具有在其间延伸的织物以提供机翼表面。 支撑构件沿着空气动力学中心横向于每个翼部的主体部分延伸，以使翼部被张紧和刚化，以便为翼部提供正弧形并形成翼型。

公开(公告)号：US07648105B2

公开(公告)日：2010-01-19

申请号：US11645029

申请日：2006-12-26

Applicant: Storm Dunker ,  Martin Gilbert

Inventor： Storm Dunker ,  Martin Gilbert

IPC: B64D17/38 ,  B64D17/00

CPC classification number: B64D17/62 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/128 ,  B64C2201/145 ,  B64D17/34

Abstract: A deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed.

Abstract translation: 与用于精密货物运送的降落伞的空中引导单元（AGU）一起使用的部署制动器释放系统。 降落伞包括一端固定在顶盖边缘的部署制动线，另一端通过环形端连接到电机控制线。 马达控制线又与AGU的马达接合。 部署制动器释放系统包括至少一个钩安装件，其具有固定到AGU框架上的钩子。 展开制动管线的环形端部在索具期间与钩接合，使得在展开时，打开力施加到钩安装件而不是马达。 在全冠层膨胀后，电机通过电机控制线拉动制动线环路端部，将其从钩上脱离，将剩余的顶盖负载转移到AGU电机，以用于其余的飞行。 还公开了一种用于释放展开制动线的方法。

公开(公告)号：US07185851B2

公开(公告)日：2007-03-06

申请号：US10927579

申请日：2004-08-26

Applicant: Daryl B. Elam

Inventor： Daryl B. Elam

IPC: B64C1/00 ,  E04B1/34

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

Abstract: An inflatable structure constructed of flexible material that can occupy a minimal volume when in a deflated and stored condition as compared to its fully inflated and deployed configuration, has sufficient structural rigidity to function as a wing when deployed. The wing includes an array of inflatable chambers with generally circular cross-sections. The chambers are spaced a particular distance between their centers and held in that spacing by an outer wing skin. For equal cross-sectional diameter chambers this distance is less than the diameter. When the chambers are inflated the close spacing causes tension in the opposing surfaces to create a rigid structure.

Abstract translation: 与其完全膨胀和展开的构造相比，当处于放气和储存状态时可以占据最小体积的柔性材料构成的充气结构在展开时具有足够的结构刚度用作翼。 机翼包括具有大致圆形横截面的可充气室阵列。 这些室在它们的中心之间隔开特定的距离，并通过外翼皮保持在该间隔中。 对于等截面直径的腔室，该距离小于直径。 当室被充气时，紧密的间隔在相对的表面中产生张力以产生刚性结构。

公开(公告)号：US20060226280A1

公开(公告)日：2006-10-12

申请号：US11305524

申请日：2005-12-16

Applicant: James Alman

Inventor： James Alman

IPC: B64C1/00 ,  B64C3/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203

Abstract: An unmanned aerial vehicle (UAV) having a design for optimum stowability and low cost. The UAV having a collapsible wing section which can be easily removed from the fuselage, allowing for quick assembly and disassembly and ease of portability. The unmanned aerial vehicle includes a primary wing assembly, a fuselage, a means for propelling the unmanned aerial vehicle, and means for remotely controlling the unmanned aerial vehicle. The primary wing assembly includes a wing having a center spar and two outwardly diverging side spars. The wing also has a pliable flexible material supported by the center spar and the at least two outwardly diverging side spars. The pylon is connected to the wing and supports the wing. The fuselage is connected to the pylon such that the pylon extends away from the fuselage and spaces the wing a distance from the fuselage. The fuselage includes a tail having a rudder located along a trailing edge and elevators located along the trailing edge.

Abstract translation: 无人飞行器（UAV）具有最佳的可收藏性和低成本的设计。 无人机具有可折叠的机翼部分，可以方便地从机身中移除，从而实现快速组装和拆卸，便于携带。 无人飞行器包括主翼组件，机身，用于推动无人驾驶飞行器的装置，以及用于远程控制无人驾驶飞行器的装置。 主翼组件包括具有中心翼梁和两个向外发散的侧翼的翼。 机翼还具有由中心翼梁和至少两个向外发散的侧翼支撑的柔韧的柔性材料。 塔架连接到机翼并支撑机翼。 机身连接到挂架，使得吊架远离机身延伸，并将机翼与机身隔开一段距离。 机身包括尾部，尾部沿着后缘设有方向舵，沿着后缘设有电梯。

公开(公告)号：US06892981B2

公开(公告)日：2005-05-17

申请号：US10408981

申请日：2003-04-08

Applicant: Jay Lipeles

Inventor： Jay Lipeles

IPC: B64C3/30 ,  B64C3/56 ,  B64C39/02 ,  B64C39/10 ,  B64D33/04 ,  B64C39/00

CPC classification number: B64C39/024 ,  B64C3/30 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/105 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  B64C2201/22 ,  B64D33/04 ,  B64D2033/045

Abstract: The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Abstract translation: Duffel Bag飞机是一种充气飞翼无人机载机（UAV）。 机身将会容纳除翅膀之外的所有东西。 机翼可以卷绕在机身周围，当放气以便于运输时，例如通过携带在行李箱中，成为小包装。 织物结构，具有冷却排气的小型内燃机和机翼翘曲控制相结合，使飞机廉价而且非常隐蔽。 所有通常的签名已经被压制，这允许它用于在战斗条件下从近距离观察。 这架飞机的控制是通过扭转机翼来实现的，并补充了稳定性增强。

公开(公告)号：US06793172B2

公开(公告)日：2004-09-21

申请号：US10296137

申请日：2003-06-30

Applicant: Lance A. Liotta

Inventor： Lance A. Liotta

IPC: B64C300

CPC classification number: B64C39/066 ,  A63H27/00 ,  B64C39/028 ,  B64C2201/105 ,  B64C2201/107

Abstract: An aircraft which is designed for remote controlled slow flight, indoor or in a small outdoor yard or field. The aerial lifting body is defined by a series of lightweight planar or thin airfoil surfaces (A1, A2, A3, A4) arranged in a radially symmetrical configuration. Suspended within the cavity (O) formed by the thin airfoil surfaces (A1, A2, A3, A4) is a thrust generating propeller system (C) that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity (O) for steering. Lifting, stability, turning, and general control of the direction of motion in flight is accomplished without any formal wings, rudder, tail, or control surfaces.

Abstract translation: 一种专为遥控慢速飞行，室内或室外小型场地设计的飞机。 升降体由一系列以径向对称构造布置的轻型平面或薄型翼型表面（A1，A2，A3，A4）限定。 悬挂在由薄翼面（A1，A2，A3，A4）形成的空腔（O）内的是推力发生螺旋桨系统（C），其向上倾斜并且可以远程调节，以便改变推力角 在腔（O）内的向量用于转向。 飞行中的运动方向的提升，稳定性，转向和一般控制是在没有任何正式的机翼，方向舵，尾翼或控制面的情况下完成的。

公开(公告)号：US20020193914A1

公开(公告)日：2002-12-19

申请号：US10045777

申请日：2002-01-11

Inventor： Tony L. Talbert ,  John Mark Kulo

IPC: B64C013/00

CPC classification number: B64C13/50 ,  B64C31/036 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D47/08

Abstract: A remote-control powered parafoil aircraft has an aircraft body (1) that is engine powered and hung with lines (2) from an air-expandable wing (3, 30). The lines include control lines (15) with which air flow and aerodynamic shape of the air-expandable wing are variable selectively from a foil controller (18, 19, 20) on the aircraft body for flight-mode control. Sight from a television camera (8) on the aircraft body is televised to a control unit (9) from which control data is transmitted selectively from proximate the control unit to the foil controller (14) with a multi-axis joystick or similar control, to an engine (6) on the parafoil body from an engine controller (24) and to an item servo (29) for control of optional items (45) on the aircraft body.

Abstract translation: 遥控动力的parafoil飞机具有发动机动力并悬挂有来自可膨胀翼（3,30）的线（2）的飞机主体（1）。 这些管线包括控制线（15），空气膨胀翼的空气流动和空气动力学形状可选择性地从飞行器体上的箔控制器（18,19,20）可变地进行飞行模式控制。 来自飞机机体上的电视摄像机（8）的视线被电视传送到控制单元（9），控制数据通过多轴操纵杆或类似的控制从控制单元的附近被选择性地发送到箔片控制器（14） 从发动机控制器（24）到达副翼车体上的发动机（6）和用于控制飞机主体上的可选项（45）的物品伺服（29）。

公开(公告)号：US6142421A

公开(公告)日：2000-11-07

申请号：US231368

申请日：1999-01-13

Applicant: Miles R. Palmer

Inventor： Miles R. Palmer

IPC: B64C39/02 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00 ,  F42B15/00 ,  B64C39/00 ,  B64D37/02

CPC classification number: B64D37/12 ,  B64C39/024 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D39/00 ,  F42B15/00 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205

Abstract: A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location. The vehicle includes a fuselage, a retractable hook with a hook sensor to detect when a fuel bladder is hooked and the loop size has been reduced by the reel mechanism, a fuel bladder stowage chamber within the fuselage, a fuel intake tube capable of drawing fuel from the fuel bladder stowed in the stowage chamber, a retraction mechanism to retract the retractable hook, a fuel transfer mechanism to transfer fuel from the fuel bladder into an internal fuel tank, and a fuel bladder discard mechanism to discard the fuel bladder after the fuel has been drawn from the fuel bladder.

Abstract translation: 车辆加油系统包括航空车辆和燃料囊系统。 燃料囊系统包括燃料囊，预定环尺寸的拾取环，卷绕机构，用于缩回拾取环的至少一侧以减小环的尺寸;阻挡传感器，用于感测拾取环何时已被钩住 可伸缩钩，启动卷轴机构的阻塞传感器，用于感测环路的随机取向的罗盘，用于感测回路位置的无线电导航接收器，以及发送器，以发送随机取向和位置。 车辆包括机身，具有钩传感器的可伸缩钩，用于检测燃料囊何时被钩住，并且通过卷轴机构减小了环路尺寸，机身内部的燃料囊存放室，能够吸引燃料的燃料进入管 从装载在储存室中的燃料气囊，收回缩回钩的缩回机构，用于将燃料从燃料气囊输送到内部燃料箱中的燃料转移机构，以及在燃料之后废弃燃料气囊的燃料气体排出机构 已从燃油囊中抽出。