公开(公告)号：US20170253331A1

公开(公告)日：2017-09-07

申请号：US15383375

申请日：2016-12-19

Applicant: FUTABA CORPORATION ,  O.S.ENGINES MFG. CO., LTD.

Inventor： Shuichiro NAKASHIMA

IPC: B64C39/02 ,  B64C27/08

CPC classification number: B64C39/024 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64D35/04

Abstract: A multicopter is provided which includes an engine configured to generate rotation by burning fuel in the engine, a plurality of propellers configured to generate a lift by rotating, a rotation transmission path configured to distribute and transmit the rotation generated by the engine to the propellers.

公开(公告)号：US20170057631A1

公开(公告)日：2017-03-02

申请号：US15332391

申请日：2016-10-24

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

Inventor： William J. FREDERICKS ,  Mark D. MOORE ,  Ronald C. BUSAN ,  Paul M. ROTHHAAR ,  David D. NORTH ,  William M. LANGFORD ,  Christopher T. LAWS ,  William T HODGES ,  Zachary R. JOHNS ,  Sandy R. WEBB

IPC: B64C29/00 ,  B64D27/24 ,  B64D27/26 ,  B64C5/02 ,  B64C11/28 ,  B64C25/52 ,  B64C39/02 ,  B64C3/38 ,  B64C11/50 ,  B64C9/14

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/40 ,  B64C5/02 ,  B64C9/14 ,  B64C11/28 ,  B64C11/50 ,  B64C25/32 ,  B64C25/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  B64D27/26 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/903

Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

Abstract translation: 提供了系统，方法和装置，其将先进的车辆配置（例如先进的飞行器配置）与电力推进的输注结合在一起，从而能够在保持完全垂直起飞和着陆的同时保持四倍的范围和耐力增加（“VTOL “）和车辆的悬停能力。 实施例可以提供具有垂直起落架和巡航高效能力的车辆，而不使用地面基础设施。 一种实施方式的车辆可以包括被配置为倾斜运动范围的翼，连接到翼的第一系列电动马达，并且每个被配置成驱动相关翼翼推进器，构造成在所述运动范围内倾斜的尾部，第二系列 耦合到尾部并且每个被配置成驱动相关联的尾部螺旋桨的电动马达以及连接到第一系列电动机和第二系列电动机的电动推进系统。

公开(公告)号：US20170029131A1

公开(公告)日：2017-02-02

申请号：US15220624

申请日：2016-07-27

Applicant: Airbus Defence and Space GmbH

Inventor： Jürgen Steinwandel ,  Ning Wang ,  Michael Judas ,  Jan Van Toor

IPC: B64D35/08 ,  B64C39/02 ,  B64C29/00 ,  B64D27/24

CPC classification number: B64D35/08 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/24 ,  B64D2027/026

Abstract: A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

Abstract translation: 具有用于产生在水平方向上有效的驱动力的推进驱动器的垂直起飞飞机和用于产生在垂直方向上有效的提升力的提升驱动装置包括用于为推进驱动提供机械能的马达和 第一发电机，用于为升降机驱动提供电能。 此外，飞行器包括用于电动机的排气涡轮增压器，其中第一涡轮机由电动机的废气流驱动，其中第一涡轮机构造成为推进驱动提供机械能。

公开(公告)号：US20170015417A1

公开(公告)日：2017-01-19

申请号：US14839960

申请日：2015-08-29

Applicant: Reference Technologies Inc

Inventor： Allen Paul Bishop

IPC: B64C39/02 ,  B64C27/82 ,  B64C29/04

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C27/82 ,  B64C29/04 ,  B64C2027/8227 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64D2027/026

Abstract: A propulsion system for a ducted fan vertical takeoff and landing aircraft (VTOL) powered by multiple electric motors with two, counter rotating electric motors comprising the primary thrust generation within a ducted fan component and 3 or more external electric motors providing lift, stability and directional control of the aircraft. Through the use of counter rotating ducted fans, the aircraft does not require the need for internal stators—either fixed or adjustable angle. Power to the electric motors is sourced by either onboard batteries, a ground based power source via a ground to aircraft tether, or an on board fuel cell or combustion engine driving an alternator.

Abstract translation: 一种用于由具有两个逆向旋转电动机的多个电动机驱动的管道风扇垂直起降飞机（VTOL）的推进系统，其包括在管道风扇部件内的主要推力产生和提供升力，稳定性和定向的3个或更多个外部电动马达 控制飞机。 通过使用反向旋转管道风扇，飞机不需要内部定子 - 固定或可调角度。 电动机的功率来自车载电池，地面电源通过地面到飞机系绳，或车载燃料电池或驱动交流发电机的内燃机。

公开(公告)号：US08386095B2

公开(公告)日：2013-02-26

申请号：US12417380

申请日：2009-04-02

Applicant: David Fitzpatrick

Inventor： David Fitzpatrick

IPC: G05D1/08 ,  B64C29/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  G01R33/0206 ,  G05D1/0858

Abstract: Methods and systems are provided for using a measurement of only one axis of a three-axis magnetometer to perform at least one corrective action on an unmanned aerial vehicle (“UAV”). An exemplary embodiment comprises (i) receiving from a three-axis magnetometer a measurement representative of an attitude of a UAV, wherein the measurement is of only one axis of the magnetometer, (ii) comparing the measurement to an allowable range of attitudes, (iii) determining that the measurement is not within the allowable range of attitudes, and (iv) performing at least one corrective action on the UAV.

Abstract translation: 提供了用于仅使用三轴磁力计的一个轴的测量来对无人驾驶飞行器（UAV）执行至少一个校正动作的方法和系统。 示例性实施例包括（i）从三轴磁力计接收表示UAV姿态的测量值，其中测量仅为磁力计的一个轴，（ii）将测量值与允许的姿态范围进行比较， iii）确定测量不在允许的态度范围内，以及（iv）对UAV执行至少一个纠正措施。

公开(公告)号：US20100181416A1

公开(公告)日：2010-07-22

申请号：US11997736

申请日：2006-07-31

Applicant: Osamu Sakamoto ,  Ikuhiko Hirami ,  Hironori Nakayama

Inventor： Osamu Sakamoto ,  Ikuhiko Hirami ,  Hironori Nakayama

IPC: B64C27/06 ,  B64D33/10 ,  B64C27/04

CPC classification number: B64C39/024 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127

Abstract: An airframe (1a) having a main body (4) and a tail body, a main rotor (6) disposed above the main body (4) and driven by an engine inside the airframe (1a), and a tail rotor disposed in a rear part of the tail body (5) are provided. A pair of support legs (8, 8) at left and right sides extending downward from left and right sides in a lower part of the main body (4) and a pair of skids (9) on left and right sides provided on the lower ends of the support legs (8) and positioned out of the main body (4) in the width direction of the airframe (1a) in a front view are provided. A radiator (71) at a position more frontward than the front ends of the skids (9) in a side view, formed extendedly downward from the vicinity of a bottom surface (83) of the front part of the main body, and having wind reception surfaces oriented to the longitudinal direction of the airframe is provided. Lateral ends of the radiator (71) in the width direction of the airframe (1a) project outward beyond lateral edges of a main body bottom surface (83) in the vicinity of the radiator (71) in a front view. Further, the lateral ends (71a) of the radiator (71) are positioned inward in the width direction of the airframe (1a) within skids 9.

Abstract translation: 具有主体（4）和尾体的机身（1a），设置在主体（4）上方并由机体（1a）内的发动机驱动的主转子（6），以及设置在主体 提供尾部本体（5）的后部。 在主体（4）的下部的左侧和右侧向下延伸的一对支撑腿（8,8）和设置在下部的左侧和右侧的一对滑板（9） 提供了支撑腿（8）的端部，并且在前视图中沿着机身（1a）的宽度方向定位在主体（4）之外。 在从主体的前部的底面的附近向下延伸的位于比侧视图的滑板（9）的前端更前方的位置处的散热器（71），并且具有风 提供了朝向机身纵向方向的接收表面。 散热器（71）在机身（1a）的宽度方向上的横向端部在前视图中向外突出于散热器（71）附近的主体底面（83）的横向边缘。 此外，散热器（71）的侧端部（71a）位于滑板9内的机身（1a）的宽度方向内侧。

公开(公告)号：US07520466B2

公开(公告)日：2009-04-21

申请号：US11384167

申请日：2006-03-17

Applicant: Nicolae Bostan

Inventor： Nicolae Bostan

IPC: B64C17/00

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：US07274978B1

公开(公告)日：2007-09-25

申请号：US10782805

申请日：2004-02-23

Applicant: Ernest A. Carroll

Inventor： Ernest A. Carroll

IPC: B64D41/00

CPC classification number: B64C39/024 ,  B64C2201/044 ,  B64D2221/00

Abstract: A miniature, unmanned aircraft for acquiring digitized data, transmitting digitized data, or both, having an electrical supply system capable of sustained operation. The aircraft has a fuselage, a wing, a reciprocating piston internal combustion engine, a propeller, control surfaces for controlling flight, each operated by a respective servomechanism, a microprocessor for managing flight control, a GPS receiver, a communications radio frequency transceiver, and data handling apparatus. The data handling apparatus is any one of a data acquisition device for gathering environmental data, a data acquisition device for sensing aircraft altitude or attitude or both, a data relay station, or any combination of these. The data handling apparatus is preferably part of an enclosed module which is readily mounted to and detachable from the aircraft. The electrical supply system includes an engine driven generator, a battery disposed in parallel to the generator, and voltage reducing devices for operating various electrical power consuming components which operate at different voltage levels.

Abstract translation: 一种用于获取数字化数据，传输数字化数据或两者的微型无人飞机，具有能够持续运行的电力供应系统。 飞机具有机身，翼，往复活塞内燃机，螺旋桨，用于控制飞行的控制面，各自由相应的伺服机构操作，用于管理飞行控制的微处理器，GPS接收器，通信射频收发器和 数据处理装置。 数据处理装置是用于收集环境数据的数据获取装置，用于感测飞机高度或姿态的数据获取装置或两者的数据中继站或这些的任意组合中的任何一个。 数据处理装置优选地是容易地安装到飞机上并可从其拆卸的封闭模块的一部分。 电源系统包括发动机驱动的发电机，与发电机并联设置的电池，以及用于操作在不同电压电平下工作的各种电力消耗部件的降压装置。

公开(公告)号：US07175135B2

公开(公告)日：2007-02-13

申请号：US10759545

申请日：2004-01-16

Applicant: Brian D. Dennis ,  Brian T. McGeer ,  Cory Roeseler

Inventor： Brian D. Dennis ,  Brian T. McGeer ,  Cory Roeseler

IPC: B64F1/02

CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for capturing and constraining motion of unmanned aircraft and other flight devices or projectiles. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. A trigger mechanism coupled to the recovery line can actuate a hoist device to reduce slack in the recovery line. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft on the recovery line.

Abstract translation: 用于捕获和限制无人驾驶飞机和其他飞行装置或射弹的运动的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 联接到回收管线的触发机构可以启动提升装置以减少回收管线中的松弛。 耦合到回收管线的张紧装置可以吸收与飞机在回收管线上的冲击相关联的力。

公开(公告)号：US07149611B2

公开(公告)日：2006-12-12

申请号：US10639267

申请日：2003-08-12

Applicant: Michael S. Beck ,  Wendell H. Chun ,  Jon T. Stinchcomb

Inventor： Michael S. Beck ,  Wendell H. Chun ,  Jon T. Stinchcomb

IPC: G01M17/00

CPC classification number: B64C39/028 ,  B60K7/0007 ,  B60K17/046 ,  B60K17/356 ,  B60T1/062 ,  B62D61/10 ,  B62D61/12 ,  B64B1/50 ,  B64C27/20 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/148 ,  B64C2201/162 ,  B64C2201/208

Abstract: A virtual sensor mast for a ground vehicle and a method for operating a ground vehicle using a virtual sensor mast are disclosed. The virtual sensor mast includes an unmanned airborne vehicle capable of lifting itself from the ground vehicle upon deployment therefrom; a sensor suite mounted to the unmanned airborne vehicle; and a tether between the unmanned airborne vehicle and the ground vehicle over which the sensor suite is capable of communicating sensed data upon deployment. The method includes elevating a tethered unmanned airborne vehicle from the ground vehicle to a predetermined height; sensing environmental conditions surrounding the ground vehicle; and terminating the deployment.

Abstract translation: 公开了一种用于地面车辆的虚拟传感器桅杆和使用虚拟传感器桅杆操作地面车辆的方法。 虚拟传感器桅杆包括能够在其从其展开时从地面车辆提升自身的无人机载机; 安装在无人机载体上的传感器套件; 以及在无人驾驶的机载车辆和地面车辆之间的系绳，传感器套件能够在部署时传送感测数据。 该方法包括：将有系带的无人机载体从地面车辆升高到预定的高度; 感测地面车辆周围的环境条件; 并终止部署。