公开(公告)号：US20170066531A1

公开(公告)日：2017-03-09

申请号：US15261780

申请日：2016-09-09

Applicant: Endurant Systems, LLC

Inventor： Gregory Leonard McAdoo

IPC: B64C39/02 ,  H02K7/18 ,  B64D27/24 ,  B64D45/00 ,  B64C29/00 ,  B64D27/04

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C27/26 ,  B64C29/0033 ,  B64C39/04 ,  B64C2201/021 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/141 ,  B64D27/04 ,  B64D27/24 ,  B64D45/00 ,  B64D2027/026 ,  B64D2045/0085 ,  B64D2221/00 ,  H02J7/14 ,  H02J7/34 ,  H02K7/1815 ,  Y02T50/64

Abstract: UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

Abstract translation: 公开了UAV内燃机的UAV配置和电池增加以及相关的系统和方法。 代表性的配置包括机身，相对于机身联接并可枢转的第一和第二翼，以及由机身承载的多个提升转子。 代表性的电池增加装置包括直流动力马达，电子速度控制器和耦合到电子速度控制器的发电机组子系统。 发电机组子系统可以包括电池组，交流发电机和电动机控制器，其具有相位控制电路，该相位控制电路可配置为整流来自交流发电机的多相交流输出，以产生经直流供电的电动机的整流直流馈电。 电机控制器可配置为从电池组中抽取直流电源，以产生整流的直流电源。

公开(公告)号：US20160369758A1

公开(公告)日：2016-12-22

申请号：US14744822

申请日：2015-06-19

Applicant: Honeywell International Inc.

Inventor： Tyler Jeppesen ,  Michael Rawson ,  Timothy Way ,  James Nickerson

IPC: F02M37/02 ,  F02M37/00 ,  B01D19/00

CPC classification number: F02M37/02 ,  B01D19/00 ,  B01D19/0036 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64D37/16 ,  B64F1/28 ,  F02M37/0076

Abstract: In some examples, a system configured to remove at least some air and other gases that are dissolved in fuel prior to introducing the fuel into a closed fuel system, such as a closed fuel system of an unmanned aerial vehicle. The system includes a vacuum chamber configured to contain a fuel, a vacuum source attached lo the vacuum chamber and configured to draw a vacuum on a headspace over the fuel in the vacuum chamber, and a fuel pump configured to pump the fuel from the vacuum chamber into a closed fuel container without introducing air into the closed fuel container. In some examples, the pump introduces a fuel substantially free of dissolved gases into the closed fuel system.

Abstract translation: 在一些示例中，系统构造成在将燃料引入封闭的燃料系统（诸如无人驾驶飞行器的封闭燃料系统）之前，去除溶解在燃料中的至少一些空气和其它气体。 该系统包括被配置为容纳燃料的真空室，附接在真空室上的真空源，并被配置成在真空室中的燃料上方的顶部空间上抽真空;以及燃料泵，构造成从真空室泵送燃料 进入封闭的燃料容器而不将空气引入封闭的燃料容器中。 在一些示例中，泵将基本上不含溶解气体的燃料引入封闭的燃料系统中。

公开(公告)号：US20160200436A1

公开(公告)日：2016-07-14

申请号：US15080167

申请日：2016-03-24

Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： David D. North ,  Mark J. Aull ,  William J. Fredericks ,  Mark D. Moore ,  Paul M. Rothhaar ,  WILLIAM T. Hodges ,  Zachary R. Johns

IPC: B64C29/00 ,  B64C39/02 ,  B64C5/02 ,  B64C25/52 ,  B64D27/24 ,  B64C3/40

CPC classification number: B64C29/0033 ,  B64C5/02 ,  B64C25/52 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64D27/24 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64

Abstract: Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.

Abstract translation: 系统，方法和设备提供诸如飞行器的车辆，其具有被配置为用作用于垂直起飞和着陆（“垂直起落架”）和用于向前飞行的固定翼车辆的三重起重机的转子。 一个转子可以安装在车身机身的前部，并由致动器控制的铰链结构从水平位置倾斜到垂直位置。 两个附加的转子可以安装在车辆尾部结构的水平表面上，其转子轴线垂直于机身。 对于车辆的前进飞行，前转子可以向下旋转，使得前转子轴线可以沿着机身水平定向，并且前转子可以用作螺旋桨。 对于垂直飞行，前转子可以向上旋转，使得前转子轴线可以垂直定向到机身，而尾转子可以被启动。

公开(公告)号：US20100243815A1

公开(公告)日：2010-09-30

申请号：US12415463

申请日：2009-03-31

Applicant: Kimberly Wong ,  Armand Losinski

Inventor： Kimberly Wong ,  Armand Losinski

IPC: B64D47/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64D1/02 ,  F16B21/02

Abstract: A payload quick release mechanism for an unmanned aerial vehicle is provided. This mechanism is affixed to a structure on the unmanned aerial vehicle, and allows for quick attachment and removal of a payload from the unmanned aerial vehicle. The attachment device comprises a body with a perimeter and a plurality of arms that extend from the body perimeter. Each arm comprises an indented section, within which a tab extending from the payload top may be placed. When the payload tab rests within the indented section, the payload is prevented from translation and is attached to the mechanism.

Abstract translation: 提供了一种用于无人机的有效载荷快速释放机构。 该机构固定在无人驾驶飞行器上的结构上，并允许从无人驾驶飞行器快速附接和移除有效载荷。 附接装置包括具有周边的主体和从主体周边延伸的多个臂。 每个臂包括凹入部分，其中可以放置从有效载荷顶部延伸的突出部。 当有效载荷标签搁置在缩进部分内时，防止有效载荷翻转并附着在机构上。

公开(公告)号：US07712702B2

公开(公告)日：2010-05-11

申请号：US11603810

申请日：2006-11-21

Applicant: Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler

IPC: 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 can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion 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 aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

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，飞行器可以从包括沿发射导向装置移动的发射台的装置发射。 当滑架和/或发射引导件的部分相对于彼此移动时，托架可以加速。 由发射托架携带的夹具可以具有至少一个与飞行器接触的抓握部分，同时发射托架沿着发射轴加速。 当发射架减速时，至少一个把手部分可以与飞行器脱离接触，释放飞机起飞。 制动器可以在发射后阻止夹具的运动。

公开(公告)号：US07658347B2

公开(公告)日：2010-02-09

申请号：US11492490

申请日：2006-07-25

Applicant: Emray R. Goossen ,  Glen A. Mantych ,  William T. Campbell

Inventor： Emray R. Goossen ,  Glen A. Mantych ,  William T. Campbell

IPC: B64F1/04

CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/201

Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.

Abstract translation: 微型飞行器（MAV）启动系统，提供组合功能：敏感车辆部件的包装保护，机械起动组件和发射台。 优选实施例包括容器和容器盖，其中MAV夹在盖上。 还设置在容器盖上的是起动组件。 将附加的MAV作为发射台的盖子从容器中取出，放在地面上，MAV以起动机构启动并启动。 这种布置可最大限度地减少操作人员的身体风险，最大限度地减少总体MAV系统的重量，消耗操作员运输系统的最小空间，并消除对电池更换或充电的电源线的依赖。

公开(公告)号：US20100012790A1

公开(公告)日：2010-01-21

申请号：US12426162

申请日：2009-04-17

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C29/04

CPC classification number: B64C3/385 ,  B64C17/06 ,  B64C27/20 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/14

Abstract: A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

Abstract translation: 一架垂直起降（VTOL）的空中客车。 机动车可以载人或无人驾驶。 在一个实施例中，空中交通工具包括安装在机身中的两个被覆盖的螺旋桨，机身和陀螺仪稳定盘。 陀螺稳定盘可以被配置成通过足够的质量和/或足够的角速度来提供足够的角动量，使得在飞行的各个阶段期间航空器的陀螺仪稳定。 在一个实施例中，机身固定地附接到被覆盖的螺旋桨。 在另一个实施例中，被覆盖的螺旋桨可枢转地安装在机身上。

公开(公告)号：US07542828B2

公开(公告)日：2009-06-02

申请号：US11160645

申请日：2005-07-01

Applicant: Daniel W. Steele ,  Joseph R. Chovan

Inventor： Daniel W. Steele ,  Joseph R. Chovan

IPC: G01C23/00 ,  B64C13/20

CPC classification number: B64D7/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165

Abstract: A small, reusable interceptor unmanned air vehicle (UAV), an avionics control system for the UAV, a design method for the UAV and a method for controlling the UAV, for interdiction of small scale air, water and ground threats. The UAV includes a high performance airframe with integrated weapon and avionics platforms. Design of the UAV first involves the selection of a suitable weapon, then the design of the interceptor airframe to achieve weapon aiming via airframe maneuvering. The UAV utilizes an avionics control system that is vehicle-centric and, as such, provides for a high degree of autonomous control of the UAV. A situational awareness processor has access to a suite of disparate sensors that provide data for intelligently (autonomously) carrying out various mission scenarios. A flight control processor operationally integrated with the situational awareness processor includes a pilot controller and an autopilot controller for flying and maneuvering the UAV.

Abstract translation: 一种小型，可重复使用的拦截无人机（UAV），无人机的航空电子控制系统，无人机的设计方法和无人机的控制方法，阻止小规模空中，水和地面威胁。 无人机包括具有集成武器和航空电子平台的高性能机身。 无人机的设计首先涉及选择合适的武器，然后设计拦截机体，以通过机身操纵实现武器瞄准。 无人机使用以车辆为中心的航空电子控制系统，因此提供了对UAV的高度自主控制。 情境感知处理器可以访问一套不同的传感器，可以智能地（自主地）执行各种任务场景。 与情境感知处理器可操作地集成的飞行控制处理器包括飞行员控制器和用于飞行和操纵无人机的自动驾驶仪控制器。

公开(公告)号：US07377470B2

公开(公告)日：2008-05-27

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：US07331546B2

公开(公告)日：2008-02-19

申请号：US11510013

申请日：2006-08-25

Applicant: Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn J. Mitryk ,  Frank J. Boria ,  Mujahid Abdulrahim

Inventor： Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn J. Mitryk ,  Frank J. Boria ,  Mujahid Abdulrahim

IPC: B64C3/56

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过从管中简单地释放微型飞行器而从管展开。