公开(公告)号：US20070084971A1

公开(公告)日：2007-04-19

申请号：US11252185

申请日：2005-10-18

Applicant: Haru Miyake

Inventor： Haru Miyake

IPC: B64C13/20

CPC classification number: B64C13/20 ,  A63H27/007 ,  A63H27/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

Abstract translation: 无线控制飞机包括飞行单元和地面控制器，其通过通信部分连接到飞行单元并飞行飞行单元。 飞行单元包括主体，安装在主体上的驱动部分，当由驱动部驱动时产生推进力的推进装置，包括多个翼元件的主翼，其安装成能够与 相对于彼此相对的改变主翼的有效面积而改变翼元件的相对位置的开闭机构，以及选择性地保持和降低载荷的下落装置。 通过改变主翼的有效面积，可以改变飞行速度，因此可以减小用于旋转推进装置的驱动部的容量和尺寸。

公开(公告)号：US20020190157A1

公开(公告)日：2002-12-19

申请号：US10168588

申请日：2002-06-24

Inventor： Jean Asseline ,  George De Noni

IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00 ,  B64C007/00

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: This invention relates to a small-sized radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, said device enabling short take-off and landing and flying at maximum speed of 35 Km/h. The device comprises a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6), the base being a welded one-piece element and comprising the engine, the airscrew, a tank and the radio control, the apex being a welded one-piece element, the lower plane and the two lateral planes comprising spars (11, 12) at least assembled at the base and at the apex, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires, the wings (13) being a caisson-type supple parachute, said wings being connected to the pod in an adjustable fashion by two front slings (17), two braking slings (18) acting on the two flaps/ailerons.

Abstract translation: 本发明涉及一种由具有用于遥感的推进式螺旋桨（19）的热引擎（20）推进的小型无线电控制飞行装置，所述装置能够以35Km / h的最大速度进行短时起飞和着陆和飞行 。 该装置包括荚和翼，所述荚（1）是刚性三轮车，通过基本上棱锥形的夹具与后基部（2）和前顶点（7），下平面（3），两个侧平面（4， 5）和上平面（6），底座是焊接的整体元件，包括发动机，螺旋桨，水箱和无线电控制器，顶点是焊接的一体元件，下平面和两个 包括至少在基部和顶点处组装的翼梁（11,12）的横向平面，所述下平面在其三个端角处包括两个后轮（8）和前轮（9），所述前轮设置成突出 朝向顶端的前部并且车轮是低压轮胎，翼（13）是沉箱式柔软的降落伞，所述翼以可调节的方式通过两个前吊索（17），两个制动吊索（ 18）作用于两个翼片/副翼。

公开(公告)号：US06322021B1

公开(公告)日：2001-11-27

申请号：US09593229

申请日：2000-06-14

Applicant: Jeffrey A. Fisher ,  Edward V. Miller

Inventor： Jeffrey A. Fisher ,  Edward V. Miller

IPC: G64C3102

CPC classification number: B64C31/024 ,  B64C31/032 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/044 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  B64D5/00 ,  Y10S244/902 ,  Y10S244/903

Abstract: A deployable wing that is folded so as to fit into a carrier such as an airplane that is released and automatically with the aid of parachutes to deploy and fly a given distance without assistance other than steering to reach a given destination and a propeller driven by a gas powered engine is actuated to propel the wing an extended distance. A guard is disposed adjacent to the propeller to assure that the lines of the parachutes do not get tangled into the propeller blades.

Abstract translation: 可展开的机翼，其被折叠以便装配在诸如飞机的载体中，并且借助于降落伞来自动地部署和飞行给定距离而不需要辅助而不是转向以达到给定的目的地并由螺旋桨驱动的螺旋桨 气动发动机被致动以推动机翼延长距离。 护翼与螺旋桨相邻设置，以确保降落伞的线条不会缠绕到螺旋桨叶片中。

公开(公告)号：US20170043882A1

公开(公告)日：2017-02-16

申请号：US15227507

申请日：2016-08-03

Applicant: DRONES LATAM SRL

Inventor： Alejandro RETTIG ,  Ianai URWICZ ,  German ZUCCOLI

IPC: B64D47/08 ,  B64C39/02 ,  B64D17/02 ,  H04N5/225

CPC classification number: B64D47/08 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/02 ,  B64C2201/107 ,  B64C2201/127 ,  B64D17/02 ,  H04N5/2252 ,  H04N5/2257

Abstract: An apparatus for capturing aerial view images via an image capturing device is provided. The apparatus includes a base; a housing defining a cavity allowing for insertion of the image capturing device, wherein the housing is engaged with the base; at least one extension member, each extension member including an upper end and a lower end, wherein the lower end of each extension member is engaged with the base, wherein each extension member extends upwardly from the base; and an air resisting element engaged with the upper end of each extension member.

Abstract translation: 提供一种用于通过图像捕获装置捕获鸟瞰图的装置。 该装置包括基座; 壳体，其限定允许插入图像捕获装置的腔体，其中所述壳体与所述基座接合; 至少一个延伸构件，每个延伸构件包括上端和下端，其中每个延伸构件的下端与基座接合，其中每个延伸构件从基部向上延伸; 以及与每个延伸构件的上端接合的防气元件。

公开(公告)号：US20150353196A1

公开(公告)日：2015-12-10

申请号：US14733962

申请日：2015-06-09

Applicant: Izak Jan van Cruyningen ,  Robert Van Wart

Inventor： Izak Jan van Cruyningen ,  Robert Van Wart

IPC: B64C39/02 ,  G01R31/40 ,  G01R29/08

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

Abstract: FIG. 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的机身10，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和检查摄像机20，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 无论自动驾驶仪，GPS信号或无线电链路的状态如何，外部机身10不能飞行而不部署降落伞18。

公开(公告)号：US20150329204A1

公开(公告)日：2015-11-19

申请号：US14281862

申请日：2014-05-19

Applicant: Brian Dale Nelson

Inventor： Brian Dale Nelson

IPC: 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：US08855838B2

公开(公告)日：2014-10-07

申请号：US13381197

申请日：2009-10-28

Applicant: Bernard Berthier

Inventor： Bernard Berthier

IPC: G06F19/00 ,  G05D1/00 ,  G05D1/08 ,  G05D3/00 ,  B64C39/02 ,  B64C31/036

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.

Abstract translation: 本发明涉及一种具有柔性翼型的飞行器的自动起飞方法，该飞行器包括通过从翼型装配线路悬挂的滑架。 根据所述方法：托架具有控制所述索具线的自动驾驶控制致动器; 翼面设置有翼型姿态传感器，包括双轴加速度计和双轴率陀螺仪，其能够定义相对于地面的翼型参考框架的位置，以及用于与所述自动驾驶仪通信的装置; 在起飞时，为了控制所述致动器，从所述翼型姿态传感器接收信息并传送到所述自动驾驶仪。 本发明还涉及一种用于实现所述方法的翼型件，包括具有带有双轴加速度计和双轴率陀螺仪的​​惯性单元的翼型姿态传感器和用于与自动驾驶仪通信的装置。 本发明还涉及一种包括这种翼型的飞行器。

公开(公告)号：US20130299634A1

公开(公告)日：2013-11-14

申请号：US13939860

申请日：2013-07-11

Applicant: Roy A. Haggard

Inventor： Roy A. Haggard

IPC: B64D1/00

CPC classification number: B64D1/00 ,  B64C2201/107 ,  B64C2201/182 ,  B64D1/22 ,  B64D3/00 ,  B64D3/02

Abstract: A grapple assembly suspended as an external load from an associated flying vehicle includes a frame member secured to an associated load line suspended from the associated vehicle. The frame member includes a first section, a second section, and a hinge joint connecting the first section to the second section. A grapple mechanism is mounted to the frame member second section. If desired, an aerodynamic body can be mounted to the frame member so as to encase at least a portion of the frame member. A release mechanism can be provided for jettisoning at least a portion of the aerodynamic body. The release mechanism can be triggered by an operator who can be stationed in the flying vehicle.

Abstract translation: 作为来自相关联的飞行车辆的外部负载悬挂的抓斗组件包括固定到从相关联的车辆悬挂的相关联的负载线的框架构件。 框架构件包括第一部分，第二部分和将第一部分连接到第二部分的铰链接头。 抓斗机构安装到框架构件第二部分。 如果需要，可以将空气动力体安装到框架构件，以便包围框架构件的至少一部分。 可以提供释放机构以用于排放空气动力体的至少一部分。 释放机构可以由可以驻扎在飞行器中的操作者触发。

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。