公开(公告)号：US20090026319A1

公开(公告)日：2009-01-29

申请号：US12222485

申请日：2008-08-11

Applicant: Edward Strong

Inventor： Edward Strong

IPC: B64D17/00

CPC classification number: B64D17/54 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/128 ,  B64C2201/141 ,  B64D1/08 ,  B64D17/08 ,  B64D17/44 ,  B64D17/64 ,  B64D17/74

Abstract: An aerial delivery system including a ram-air parachute, one or more recovery parachutes, a mantle removably attached to a cargo, and a controller operably connected to the mantle, the ram-air parachute, and the one or more recovery parachutes. The controller may be configured to receive location information associated with a target, receive information related to an ambient condition, determine a recovery parachute opening point based on the target information and the ambient condition, and cause a navigation of the aerial delivery system to the determined recovery parachute opening point.

Abstract translation: 一种空中输送系统，包括冲击空气降落伞，一个或多个回收降落伞，可移除地附接到货物的地幔，以及可操作地连接到地幔，冲击空降落伞和一个或多个恢复降落伞的控制器。 控制器可以被配置为接收与目标相关联的位置信息，接收与环境条件相关的信息，基于目标信息和环境条件来确定恢复降落伞开放点，并且使空中传送系统导航到所确定的 恢复降落伞开放点。

公开(公告)号：US3980259A

公开(公告)日：1976-09-14

申请号：US564639

申请日：1975-04-02

Applicant: Richard David Greenhalgh ,  Ronald Alexander Saunders ,  George Reginald Seyfang

Inventor： Richard David Greenhalgh ,  Ronald Alexander Saunders ,  George Reginald Seyfang

IPC: B64C39/02 ,  B64D17/80

CPC classification number: B64C39/024 ,  B64D17/80 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/182 ,  B64C2201/205 ,  Y10S244/902

Abstract: A powered remotely piloted vehicle which is not controllable at the low landing speeds necessary for landing on a platform of small area is provided with a para-foil type wing deployable at the beginning of a recovery sequence, and is further provided with a rocket ejectable line which is passed to the landing platform and winched in so that the composite flight vehicle and deployed para-foil wing is drawn towards the platform after the manner of a kite.

Abstract translation: 在低平台上不能控制的低功率遥控车辆在降落在小平台的平台上所需的底盘上设置有可在恢复顺序开始时展开的对箔型翼，并且还设置有火箭弹出线 将其传递到着陆平台并绞盘，使得复合飞行器和部署的对箔翼沿着风筝的方式被吸引到平台上。

公开(公告)号：EP3152630A1

公开(公告)日：2017-04-12

申请号：EP15806519.3

申请日：2015-06-09

Applicant: Van Cruyningen, Izak ,  Van Wart, Robert

Inventor： Van Cruyningen, Izak ,  Van Wart, Robert

IPC: G05D1/02

CPC classification number: B64C39/024 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/14 ,  G01R29/0878 ,  G01R31/085 ,  G01R31/40 ,  G05D1/101 ,  H02G1/02

Abstract: Figure 1 shows airframe 10 with electromagnetic field sensor 12, adjustable reference electromagnetic field strength 14, comparator 16, parachute 18, parachute trigger 19, and inspection camera 20 inspecting a transmission line corridor containing towers 40, 42, and 44, phase conductors 46, 48, and 50, and shield wires 52 and 54. Reference electromagnetic field strength 14 is adjusted before the flight to set the minimum electromagnetic field strength before parachute trigger 19 deploys parachute 18. The reference electromagnetic field strength 14 corresponds to a radius, and thus virtual tunnel 22, outside of which airframe 10 cannot fly without deploying parachute 18, regardless of the state of the autopilot, GPS signal, or radio link.

Abstract translation: 图。 图1示出了具有电磁场传感器12，可调参考电磁场强度14，比较器16，降落伞18，降落伞触发器19和检查照相机20的机身10，其检查包含塔40,42和44的传输线走廊，相导体46,48 和50，以及屏蔽线52和54.在飞行之前调整参考电磁场强度14，以在降落伞触发器19部署降落伞18之前设置最小电磁场强度。参考电磁场强度14对应于半径，因此虚拟 无论自动驾驶员，GPS信号或无线电链路的状态如何，机身10外不能飞行而不部署降落伞18的隧道22。

公开(公告)号：EP2521670A1

公开(公告)日：2012-11-14

申请号：EP09760232.0

申请日：2009-10-28

Applicant: Swissavia

Inventor： BERTHIER, Bernard

IPC: B64C31/036 ,  B64C39/02

CPC classification number: B64C31/036 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107

Abstract: The invention relates to an automatic takeoff method for an aircraft with a flexible airfoil, comprising a carriage suspended by rigging lines from an airfoil. According to said method: - said carriage is provided with an autopilot controlling actuators that control said rigging lines; - said airfoil is provided with an airfoil attitude sensor, comprising a biaxial accelerometer and a biaxial rate gyro, capable of defining the position of an airfoil reference frame in relation to the ground, and means for communicating with said autopilot; - during takeoff, information is received from said airfoil attitude sensor and transmitted to said autopilot for the purpose of controlling said actuators. The invention also relates to an airfoil for the implementation of said method, comprising an airfoil attitude sensor with an inertial unit with a biaxial accelerometer and a biaxial rate gyro, and means for communicating with an autopilot. The invention further relates to an aircraft comprising such an airfoil.

公开(公告)号：EP1289830A2

公开(公告)日：2003-03-12

申请号：EP01944161.7

申请日：2001-05-23

Applicant: LIOTTA, Lance A.

Inventor： LIOTTA, Lance A.

IPC: B64C3/00

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.

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。