公开(公告)号：WO2014011296A2

公开(公告)日：2014-01-16

申请号：PCT/US2013/036750

申请日：2013-04-16

Applicant: WINTEC ARROWMAKER, INC.

Inventor： JONES, John, Charles ,  GRIGORYEV, Artem, Igorevich ,  ESPINOSA, Luis, Carlos

CPC classification number: B64F1/06 ,  B64C2201/084

Abstract: A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured to support the cradle above the base. The UAS launcher includes a launch control system configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal. The UAS launcher also includes one or more elastic members configured to engage the carriage assembly and the rail assembly. Once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members. Release of the carriage assembly enables force generated by strain of the elastic members to propel the carriage assembly toward a launch position.

Abstract translation: 便携式无人航空系统发射器（UAS）发射器包括具有内部轨道的轨道组件和具有被配置为在内部轨道内平移的基座的滑架组件。 托架组件还包括构造成支撑UAS的托架和构造成将托架支撑在基座上方的托架。 UAS启动器包括启动控制系统，该启动控制系统被配置为将滑架组件固定在启动就绪位置，直到启动控制系统接收启动信号。 UAS发射器还包括一个或多个弹性构件，所述弹性构件构造成接合滑架组件和导轨组件。 一旦滑架组件转换到准备就绪位置，通过一个或多个弹性构件将应变施加到滑架组件。 滑架组件的释放使得由弹性构件的应变产生的力将滑架组件推向发射位置。

公开(公告)号：WO2005016753A3

公开(公告)日：2006-10-19

申请号：PCT/US2004009988

申请日：2004-04-01

Applicant: INSITU GROUP INC ,  ROESELER CORY ,  MCGEER BRIAN T ,  VON FLOTOW ANDREAS H

Inventor： ROESELER CORY ,  MCGEER BRIAN T ,  VON FLOTOW ANDREAS H

IPC: B64F1/06 ,  B64C39/02 ,  B64F20060101 ,  B64F1/02 ,  B64F1/04

CPC classification number: B64C39/024 ,  B64C2201/084

Abstract: Methods and apparatuses for cable launching airborne devices (e.g., unmanned aircraft) are disclosed. In one embodiment, an apparatus includes an elongated structure, e.g., a tower, boom or derrick. At least one flexible elongated member (e.g., a cable or rope) can be attached toward one end to the structure and toward another end to the ground or another structure to form an elongated launch path. A cradle, which can carry the airborne device, can also be movably attached to the flexible elongated member and can be accelerated along the launch path. As the cradle decelerates, the aircraft can be released into flight.

Abstract translation: 公开了用于电缆发射机载装置（例如，无人飞行器）的方法和装置。 在一个实施例中，装置包括细长结构，例如塔架，起重臂或井架。 至少一个柔性细长构件（例如，电缆或绳索）可以朝向结构的一端并且朝向地面或另一结构的另一端附接以形成细长的发射路径。 可以携带机载装置的支架也可以可移动地附接到柔性细长构件并且可以沿着发射路径被加速。 当支架减速时，飞机可以释放飞行。

公开(公告)号：WO2005076788A3

公开(公告)日：2005-12-22

申请号：PCT/US2004009212

申请日：2004-03-25

Applicant: INSITU GROUP ,  MCGEER BRIAN T ,  ROESELER CORY ,  VON FLOTOW ANDREAS

Inventor： MCGEER BRIAN T ,  ROESELER CORY ,  VON FLOTOW ANDREAS

IPC: B64C3/56 ,  B64F1/06

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft (150) can be launched from an apparatus that includes a launch carriage (120) that moves along a launch axis. A gripper (180) carried by the launch carriage can have at least one grip Portion (181) in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the fuselage of the aircraft as the launch carriage (120) decelerates, releasing the aircraft (150) for takeoff.

Abstract translation: 描述了发射无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器（150）可以从包括沿着发射轴移动的发射台（120）的装置发射。 由发射托架承载的夹持器（180）可以具有与飞行器接触的至少一个手柄部分（181），同时发射托架沿着发射轴加速。 随着发射台（120）减速，至少一个把手部分可以与飞机的机身脱离接触，释放飞机（150）以起飞。

公开(公告)号：WO2005023642A3

公开(公告)日：2005-11-10

申请号：PCT/US2004004720

申请日：2004-02-19

Applicant: AAI CORP ,  MILLER STEPHEN W ,  VELAZQUEZ MATTHEW T

Inventor： MILLER STEPHEN W ,  VELAZQUEZ MATTHEW T

IPC: B64B20060101 ,  B64B1/00 ,  B64C3/56 ,  B64C39/02 ,  B64F1/04 ,  B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

Abstract translation: 提供了一种便携式无人飞行器和发射器系统，其包括具有压力管的可折叠无人驾驶飞行器; 用于容纳发射气体的发射气体储存器; 发射管，可操作地连接到发射气体储存器并且具有定位在飞行器的压力管中的自由端; 位于发射管内的自由活塞; 和一个自由活塞止动件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中并且迫使自由活塞从初始位置移动到自由活塞通过自由活塞止挡而停止的终点位置。

公开(公告)号：WO2005014390A2

公开(公告)日：2005-02-17

申请号：PCT/US2004/001033

申请日：2004-01-17

Applicant: THE INSITU GROUP ,  DENNIS, Bryan, D. ,  JACKSON, Clifford ,  MCGEER, Brian, T. ,  ROESELER, Cory ,  VONFLOTOW, Andreas, H.

Inventor： DENNIS, Bryan, D. ,  JACKSON, Clifford ,  MCGEER, Brian, T. ,  ROESELER, Cory ,  VONFLOTOW, Andreas, H.

IPC: B64B

CPC classification number: B64F1/02 ,  B63B27/26 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for assembling, launching, recovering, disassembling, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

Abstract translation: 描述了组装，发射，恢复，拆卸，捕获和存储无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由操作者很少或没有手动接合的容器组装。 容器可以包括用于控制飞行器部件的运动的引导结构。 飞机可以从包括可伸缩吊杆的装置发射。 可以扩展繁荣部署一个恢复线，以便在飞行中捕获飞机。 飞机然后可以返回到其发射平台，拆卸并存储在容器中，再次与操作员和飞机之间的很少或没有直接的手动接触。

公开(公告)号：WO02032762A2

公开(公告)日：2002-04-25

申请号：PCT/US2001/031631

申请日：2001-10-11

IPC: B64C39/02 ,  F42B15/10 ,  B64C

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 an 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。 机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温环境的高负载，并且可以承受大约16,000g的安装载荷。

公开(公告)号：WO1994016942A1

公开(公告)日：1994-08-04

申请号：PCT/US1994000590

申请日：1994-01-21

Applicant: FREEWING AIRCRAFT CORPORATION

Inventor： FREEWING AIRCRAFT CORPORATION ,  RUTAN, Elbert, L. ,  SCHMITTLE, Hugh, J.

IPC: B64C03/38

CPC classification number: B64C29/02 ,  B64C3/385 ,  B64C29/0033 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/187 ,  B64D2201/00 ,  Y10S446/901

Abstract: A VTOL/STOL free wing aircraft (100) includes a free wing (110) having wings on opposite sides of a fuselage (102) connected to one another respectively adjacent fixed wing inboard or center root sections (117) fixedly attached to the fuselage (102) for free rotation about a spanwise axis (112). Horizontal and vertical tail surfaces (138, 140) are located at the rear end of a boom assembly (120) rotatably connected to the fuselage (102). A gearing (150) or screw rod (160) arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage (102) in relation to the tail boom assembly (120) to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight.

Abstract translation: VTOL / STOL自由翼飞机（100）包括在机身（102）的相对侧上具有翅片的自由翼（110），它们分别相互连接，分别邻接固定在机身上的固定翼或固定地连接到机身的中心根部（117） 102），用于绕翼展轴线（112）自由旋转。 水平和垂直尾部表面（138,140）位于可旋转地连接到机身（102）的悬臂组件（120）的后端。 由飞行员或遥控操作员控制的传动装置（150）或螺杆（160）布置选择地相对于尾臂组件（120）相对地枢转机身（102），以使得机身能够呈现倾斜或起起落架构 以启用VTOL / STOL航班。

公开(公告)号：US20180292817A1

公开(公告)日：2018-10-11

申请号：US15565035

申请日：2016-12-07

Applicant: Intel Corporation

Inventor： Songnan Yang ,  Muhammad Abozaed ,  Rafael De La Guardia Gonzalez ,  David Gomez Gutierrez ,  Hong Wong

IPC: G05D1/00 ,  G08G5/00 ,  B64C39/02 ,  G01P5/06

CPC classification number: G05D1/0005 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/141 ,  B64F1/06 ,  G01P5/06 ,  G05D1/0088 ,  G08G5/003 ,  G08G5/0091

Abstract: Methods and apparatus for reducing energy consumed by drones during flight are disclosed. A drone includes a housing, a motor, and a route manager to generate a route for a flight of the drone based on wind data. The wind data includes turbine-generated wind data provided by turbines that detect airflows received at the turbines. The turbines are located in an area within which a segment of the flight of the drone is to occur. The route is to be followed by the drone during the flight to reduce energy consumed by the drone during the flight.

公开(公告)号：US10054939B1

公开(公告)日：2018-08-21

申请号：US14033511

申请日：2013-09-22

Applicant: Paul G. Applewhite

Inventor： Paul G. Applewhite

IPC: B64C27/82 ,  G05D1/00 ,  B64C39/02 ,  B64F1/04 ,  B64F1/06 ,  B64C29/00 ,  B64C29/02

CPC classification number: G05D1/0027 ,  B64C11/04 ,  B64C11/28 ,  B64C27/82 ,  B64C29/0083 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/08 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/126 ,  B64C2201/146 ,  B64F1/04 ,  B64F1/06 ,  G05D1/104 ,  G08G5/00 ,  G08G5/0008 ,  G08G5/0013 ,  G08G5/0069

Abstract: An improved unmanned aerial vehicular system having a rotor head assembly with any balanced number of rotary wings or blades, a generally tubular body assembly, a gimballed neck connecting the head to the body, and a navigation, communications and control unit such as for military and humanitarian operations, including payload delivery and pickup. The vehicle is generally guided using a global positioning satellite signal, and by pre-programmed or real time targeting. The vehicle is generally electrically powered and may be launched by one of (a) hand-launch, (b) air-drop, (c) catapult, (d) tube-launch, or (e) sea launch, and is capable of landing on both static and dynamic targets. Once launched, unmanned aerial vehicles may be formed into arrays on a target area and find use in surveillance, warfare, and in search-and-rescue operations.

公开(公告)号：US20180186474A1

公开(公告)日：2018-07-05

申请号：US15844226

申请日：2017-12-15

Applicant: AeroVironment, Inc.

Inventor： Guan H. Su ,  Marcos Henry Rodriguez

IPC: B64F1/04 ,  F41B11/80 ,  B64C39/02 ,  B64F1/06 ,  F41F3/042 ,  F41F3/073 ,  F41F3/00 ,  F41F3/052

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV having an exterior surface, an aerial vehicle (AV) tab extending from the exterior surface, a tube containing the UAV, the tube including a tab stop configured to controllably hinder travel of the AV tab past the tab stop, and a pair of opposing tab guides configured to position the AV tab for travel over the tab stop.