公开(公告)号：US09272784B2

公开(公告)日：2016-03-01

申请号：US14281862

申请日：2014-05-19

Applicant: Brian Dale Nelson

Inventor： Brian Dale Nelson

IPC: B64C27/08 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C27/26 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/107 ,  B64C2201/108

Abstract: An unmanned aerial vehicle (UAV) comprising a plurality of propeller drives rigidly mounted to a foldable frame with the motor rotors aligned in a vertical direction to provide a means of vertical takeoffs and landings. The foldable frame mounts a sheet sail at an angle with the horizontal that provides lift during the forward motion and tilt of the UAV. In one embodiment the shape of the sheet sail and frame are triangular with one or two propeller drives being mounted in close proximity to each of the three vertices. In another embodiment, the shape of the sheet sail and frame are triangular with one or two propeller drives being mounted in close proximity to each of the three vertices, and one or two propeller drives being mount in close proximity to the trailing edge of the spine, in between the trailing edge propeller drives. In some embodiments, the frame spars may be comprised of carbon fiber rods and the sheet sail may be comprised of ripstop nylon fabric.

Abstract translation: 一种无人驾驶飞行器（UAV），其包括刚性地安装到可折叠框架的多个螺旋桨驱动器，其中马达转子在垂直方向上对准以提供垂直起飞和降落的装置。 可折叠框架以与水平方向成一定角度安装片材帆，在无人机的向前运动和倾斜期间提供升力。 在一个实施例中，片材帆和框架的形状是三角形的，其中一个或两个螺旋桨驱动器安装在三个顶点中的每一个附近。 在另一个实施例中，片材帆和框架的形状是三角形的，其中一个或两个螺旋桨驱动器安装在三个顶点中的每一个附近，并且一个或两个螺旋桨驱动器安装在脊柱的后缘附近 在后缘螺旋桨驱动器之间。 在一些实施例中，框架翼梁可以​​由碳纤维杆组成，片材帆可以由防撕裂尼龙织物组成。

公开(公告)号：US09033281B1

公开(公告)日：2015-05-19

申请号：US13410225

申请日：2012-03-01

Applicant: Richard D. Adams

Inventor： Richard D. Adams

IPC: B64D9/00

CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/203

Abstract: A radio controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propulsion source, and in another embodiment the power and control module is suspended from a point above a propulsion source. The UAV is controlled by radio controls from a hand held controller, with actuators retracting and letting out control lines attached to the parachute in order to control direction of the parachute. The UAV may be launched from a tube using a pressurized tank with a nozzle expelling gas from the tank, the tank and nozzle towing a canister from which the UAV is deployed.

Abstract translation: 公开了一种无线电控制的无人机。 无人机包括一个降落伞，一个圆柱形的电源和控制模块垂直悬挂在降落伞下方。 在一个实施例中，推进源安装在功率和控制模块的顶部，其控制线连接到推进源下方的模块，并且在另一个实施例中，功率和控制模块从推进源上方的点悬挂。 无人机由手持控制器的无线电控制控制，执行器缩回并释放连接到降落伞的控制线，以控制降落伞的方向。 无人机可以使用加压罐从管中发射，喷嘴排出来自罐，罐和喷嘴的气体，其牵引无人机从其部署的罐。

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：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：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：US4311290A

公开(公告)日：1982-01-19

申请号：US90205

申请日：1979-11-01

Applicant: Kenneth T. Koper

Inventor： Kenneth T. Koper

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/182 ,  B64C2201/185

Abstract: Apparatus and method for recovering and arresting an aircraft or other vele. A boom is swivelly connected to a support structure via braking mechanism. The boom is pivotally connected to the brake mechanism such that it can also pivot in a second, different plane intersecting the plane of rotation of the brake mechanism. A shear pin prevents pivoting of the boom in the second plane until the boom has experienced a predetermined load in that plane. The distal end of the boom distant from the brake mechanism is provided with structure for engaging the aircraft. When the aircraft is flown at and captured by the boom, the weight and motion of the aircraft breaks the shear pin, causing the boom to move in the second plane until engaged by a stop. This rapid change in position of the engaging end of the boom in the second plane prevents the aircraft from pendulating about the boom. Forward motion of the aircraft also causes movement within the brake mechanism in the first plane which absorbs the kinetic energy of the aircraft as the boom swivels against the brake mechanism, so that the aircraft is slowed and arrested.

Abstract translation: 用于恢复和阻止飞机或其他车辆的装置和方法。 动臂通过制动机构旋转地连接到支撑结构。 吊杆枢转地连接到制动机构，使得其也可以在与制动机构的旋转平面相交的第二不同平面中枢转。 剪切销防止悬臂在第二平面中的枢转，直到悬臂在该平面中经历了预定的载荷。 离开制动机构的悬臂的远端设置有用于接合飞行器的结构。 当飞机飞行并被悬臂捕获时，飞行器的重量和运动会破坏剪切销，导致吊臂在第二平面中移动，直到停止。 在第二平面中，起重臂的接合端的这种快速变化防止飞机在吊杆周围摆动。 飞行器的前进运动也引起在第一平面内的制动机构内的运动，当悬臂靠在制动机构上转动时吸收飞行器的动能，从而使飞行器减慢和停止。