公开(公告)号：US20160332739A1

公开(公告)日：2016-11-17

申请号：US14713343

申请日：2015-05-15

Applicant: Disney Enterprises, Inc.

Inventor： Clifford Wong

IPC: B64D25/00 ,  B64C39/02

CPC classification number: B64D25/00 ,  B64C39/00 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/024 ,  B64C2201/14 ,  B64C2201/146 ,  B64C2201/18 ,  B64C2201/185

Abstract: An unmanned aerial vehicle apparatus comprises a frame. Further, the unmanned aerial vehicle apparatus comprises a propulsion mechanism coupled to the frame that propels the frame through the air. In addition, the unmanned aerial vehicle apparatus comprises a storage device that stores one or more airbags and is coupled to the frame. The unmanned aerial vehicle apparatus also comprises an inflation device coupled to the frame that receives an activation signal and inflates the one or more airbags based upon receipt of the activation signal to deploy the one or more airbags from the storage device prior to an impact of the frame with an object.

Abstract translation: 无人驾驶飞行器装置包括一个框架。 此外，无人驾驶飞行器装置包括联接到框架的推进机构，其推动框架通过空气。 此外，无人驾驶飞行器装置包括存储装置，该存储装置存储一个或多个安全气囊并且联接到该框架。 无人驾驶飞行器装置还包括联接到框架的充气装置，其接收启动信号，并且基于接收到激活信号而使一个或多个安全气囊充气，以在所述启动信号的影响之前从所述存储装置部署所述一个或多个气囊 框架与对象。

公开(公告)号：US20160318615A1

公开(公告)日：2016-11-03

申请号：US15140718

申请日：2016-04-28

Applicant: SkyFallX, LLC

Inventor： Michael Andrew Pick

IPC: B64D17/54 ,  B64C25/32 ,  B64C39/02 ,  B64D17/80

CPC classification number: B64D17/54 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/185 ,  B64D17/80

Abstract: A safety and recovery system for an unmanned aerial vehicle including a parachute holder mountable to the aerial vehicle. A parachute is disposed in the parachute holder. An actuator is engaged with the parachute holder. A flight sensor is in communication with the actuator, the flight sensor programmed to detect one or more predetermined emergency flight conditions, and transmit an emergency signal when the flight sensor detects one of the predetermined emergency flight conditions. The actuator deploys the parachute from the parachute holder when the actuator receives the emergency signal from the flight sensor. Autonomous deployment of the parachute can help minimize damage to the aerial vehicle, equipment on the aerial vehicle, or objects or persons beneath the aerial vehicle, in the event of an emergency.

Abstract translation: 一种用于无人机的安全和恢复系统，包括可安装到飞行器的降落伞支架。 降落伞放在降落伞架上。 执行机构与降落伞支架接合。 飞行传感器与致动器通信，飞行传感器被编程为检测一个或多个预定的紧急飞行条件，并且当飞行传感器检测到预定的紧急飞行状况之一时发送紧急信号。 当执行器从飞行传感器接收到紧急信号时，执行器从降落伞支架上部署降落伞。 如果发生紧急情况，自主部署降落伞可以帮助最大限度地减少飞机上的飞行器，飞机上的设备或飞行器下的物体或人员造成的损坏。

公开(公告)号：US09409644B2

公开(公告)日：2016-08-09

申请号：US14333462

申请日：2014-07-16

Applicant: Ford Global Technologies, LLC

Inventor： Joseph F. Stanek ,  John A. Lockwood

IPC: B64C39/02 ,  G05D1/00 ,  B60R16/02 ,  G08C17/00

CPC classification number: G05D1/0276 ,  B60R16/02 ,  B60W30/00 ,  B64C29/0008 ,  B64C29/0091 ,  B64C29/02 ,  B64C39/00 ,  B64C39/02 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/02 ,  B64C2201/08 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/12 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/14 ,  B64C2201/141 ,  B64C2201/18 ,  B64C2201/182 ,  B64C2201/185 ,  B64C2201/187 ,  B64C2201/20 ,  B64C2201/208 ,  B64C2230/00 ,  G05D1/0022 ,  G05D1/0088 ,  G05D1/0094 ,  G05D1/0202 ,  G05D1/0212 ,  G05D1/0231 ,  G05D1/0242 ,  G05D1/0255 ,  G05D1/0257 ,  G05D1/028 ,  G05D2201/0213 ,  G08C17/00 ,  G08G1/012 ,  G08G1/091

Abstract: This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced.

Abstract translation: 本公开总体上涉及一种汽车无人机部署系统，该系统至少包括车辆和可部署的无人机，其配置为从车辆附接和分离。 更具体地，本公开描述了当车辆以自主驾驶模式操作时彼此保持通信的车辆和无人机交换信息，使得车辆在自主驾驶模式下的性能得到增强。

公开(公告)号：US20150314881A1

公开(公告)日：2015-11-05

申请号：US14646912

申请日：2013-11-25

Applicant: WISEC LTD

Inventor： Amir Tsaliah ,  Ran Krauss

IPC: B64D17/80 ,  B64D17/72

CPC classification number: B64D17/80 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/185 ,  B64D17/72 ,  B64D17/725

Abstract: The present invention provides safety apparatus for a multi-blade aircraft, comprising an expandable and collapsible parachute assembly having a plurality of inflatable tubes, a plurality of electrically triggered gas generators connected to a support surface of a multi-blade aircraft, and an on-board control unit for initiating triggering of said plurality of gas generators, wherein an outlet end of each of said plurality of gas generators is connected to, and in fluid communication with, a bottom end of one of said plurality of tubes, allowing said parachute assembly to be fully expanded upon generation of inflating gas by each of said plurality of gas generators.

Abstract translation: 本发明提供了一种用于多叶片飞行器的安全装置，其包括具有多个可充气管的可膨胀和可折叠降落伞组件，连接到多叶片飞行器的支撑表面的多个电触发气体发生器， 用于启动所述多个气体发生器的触发的板控制单元，其中所述多个气体发生器中的每一个的出口端连接到所述多个管之一的底端并与其流体连通，允许所述降落伞组件 在由所述多个气体发生器中的每一个产生膨胀气体时完全膨胀。

公开(公告)号：US08191831B2

公开(公告)日：2012-06-05

申请号：US11992188

申请日：2005-11-30

Applicant: Ronen Nadir

Inventor： Ronen Nadir

IPC: B64D17/00 ,  B64D17/54

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/185 ,  B64D17/80

Abstract: The disclosure provides a parachute release device which may include a connecting element capable of connecting to an aircraft and to a parachute and a locking mechanism capable of releasing the connecting element from the aircraft upon being actuated by an actuator, wherein the parachute may be connected to the connecting element by a multiplicity of points, wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator and wherein the device may be suitable for use in small weights aircrafts due to its small size and weight. The disclosure further provides a method for releasing a parachute from an aircraft, the method may include activating an actuator capable of releasing a locking mechanism, wherein the locking mechanism is adapted to release a connecting element from an aircraft upon being actuated, wherein the connecting element is adapted to connect a parachute and wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator.

Abstract translation: 本公开提供了一种降落伞释放装置，其可以包括能够连接到飞机和降落伞的连接元件，以及能够由致动器致动时能够从飞行器释放连接元件的锁定机构，其中降落伞可以连接到 所述连接元件由多个点组成，其中所述锁定机构适于阻止施加到所述致动器的力，并且其中所述装置由于其小的尺寸和重量而适合用于小型重量飞机。 本发明还提供了一种用于从飞行器释放降落伞的方法，所述方法可包括激活能够释放锁定机构的致动器，其中所述锁定机构适于在致动时从飞行器释放连接元件，其中所述连接元件 适于连接降落伞，并且其中所述锁定机构适于阻止施加在所述致动器上的力。

公开(公告)号：US20100012774A1

公开(公告)日：2010-01-21

申请号：US11803720

申请日：2007-05-15

Applicant: Jerome P. Fanucci ,  Nathan Gravelle ,  Stephen A. Schoenholtz

Inventor： Jerome P. Fanucci ,  Nathan Gravelle ,  Stephen A. Schoenholtz

IPC: B64C3/56

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/128 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201 ,  F42B10/14 ,  F42B10/143 ,  F42B10/56 ,  F42B12/365 ,  F42B15/08 ,  F42B15/105

Abstract: An unmanned aerial vehicle mounts a payload section to an air delivery vehicle. The air delivery vehicle includes deployable wings and tail fins for gliding or powered flight. A set of propeller blades are provided for powered flight. The propeller blades are mounted for movement from a stowed position to deployed position extending radially from the fuselage for powered flight.

公开(公告)号：US20030155463A1

公开(公告)日：2003-08-21

申请号：US10194814

申请日：2002-07-12

Applicant: MISSION TECHNOLOGIES, INC.

Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

IPC: F41G007/00

CPC classification number: F41G3/02 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06 ,  Y02T50/82

Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

Abstract translation: 一种无人机载侦察系统，无人机载侦察系统，包括轻型便携式动力飞机和折叠式发射轨道，该飞机处于分解状态，发射导轨处于可折叠状态的箱体内，该箱体能够 由一个男人携带。 发射系统包括具有滑架组件的细长的发射轨道和用于将滑架组件从发射轨道的一端加速到另一端的推进装置。 滑架组件可释放地接合飞行器，以便将飞机从发射轨的一端推动到另一端。 推进可以是通过气缸爆炸和释放气体的弹药筒或弹性帘线。 飞机通过编程的机载计算机被引导通过空中，控制飞机的控制面和/或通过遥控。 飞机通常包含用于记录和发射从下面接地的图像的照相机。

公开(公告)号：US20030089821A1

公开(公告)日：2003-05-15

申请号：US10323512

申请日：2002-12-18

Inventor： Carlos T. Miralles ,  Bart D. Hibbs

IPC: B64C003/56

CPC classification number: B64G1/222 ,  B64C1/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/185 ,  B64C2201/203 ,  B64G1/105 ,  B64G1/62

Abstract: Disclosed is a spacecraft carrying a number of pods, each containing an aircraft that has been folded to fit in the pod. Each aircraft has a vertical stabilizer and outboard wing-portions that fold around fore-and-aft axes. Each aircraft also has a fuselage that folds around a lateral axis. The spacecraft releases one or more of the pods into an atmosphere. Each of the pods is configured with an ablative heat shield and parachutes to protect its aircraft when the pod descends through the atmosphere. The pod releases its aircraft at a desired altitude or location, and the aircraft unfolds while free-falling. The aircraft then acquires and follows a flight path, and activates scientific experiments and instruments that it carries. The aircraft relays results and readings from the experiments and instruments to the spacecraft, which in turn relays the results and readings to a mission command center.

公开(公告)号：US20030089820A1

公开(公告)日：2003-05-15

申请号：US10150726

申请日：2002-05-17

Inventor： Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland JR.

IPC: F42B015/01 ,  F42B015/10 ,  F42B015/20 ,  F42B015/22

CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load and high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单​​。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼片段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高负载和高温环境，并且可以容忍约16,000g的安装载荷。

公开(公告)号：US20030025038A1

公开(公告)日：2003-02-06

申请号：US09922167

申请日：2001-08-06

Applicant: Lockheed Martin Corporation

Inventor： Leland M. Nicolai ,  Douglas J. Robinson ,  William R. Ramsey JR.

IPC: B64D017/14 ,  B64D017/18 ,  B64D017/34

CPC classification number: G05D1/105 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D17/025 ,  B64D17/343

Abstract: A parafoil system for autonomously controlling the gliding descent of a payload/UAV from a launch point to a predetermined recovery area and manipulating the parafoil to execute a soft landing in the recovery area, a sensing means associated with the system for determining wind speed and direction, as well as altitude, heading and position of the system, a means housed within the system for processing information received from the sensing means to determine the gliding flight path from the launch point to a predetermined recovery area and the execution of a flare maneuver to achieve a soft landing, control surface means on the parafoil canopy, mechanical means coupling the information processing means with the control surface means for adjusting the control surface means to accomplish the steering to the recovery area during gliding flight and the flare maneuver during landing, and a power source in the payload/UAV.

Abstract translation: 一种用于自主地控制有效载荷/ UAV从发射点到预定恢复区域的滑翔下降并操纵石灰石以在恢复区域中执行软着陆的石蜡系统系统，与用于确定风速和方向的系统相关联的感测装置 ，以及系统的高度，航向和位置，装在系统内的装置，用于处理从感测装置接收的信息，以确定从发射点到预定恢复区域的滑行飞行路径，以及执行火炬操纵 实现软着陆，控制表面装置在parafoil冠层上，机械装置将信息处理装置与控制面相结合，用于调整控制面装置，以实现滑行飞行期间的恢复区域的转向和着陆期间的火炬机动，以及 有效载荷/无人机中的电源。