公开(公告)号：US06502787B1

公开(公告)日：2003-01-07

申请号：US10082814

申请日：2002-02-22

Applicant: Ronald Martin Barrett

Inventor： Ronald Martin Barrett

IPC: B64C2720

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C29/02 ,  B64C39/028 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162

Abstract: A vertical take-off and landing miniature aerial vehicle includes an upper fuselage segment and a lower fuselage segment that extend in opposite directions from a rotor guard assembly. A rotor rotates within the rotor guard assembly between the fuselage segments. Plural turning vanes extend from the rotor guard assembly beneath the rotor. Moreover, plural grid fins extend radially from the lower fuselage segment below the turning vanes. The aerial vehicle is capable of taking off and landing vertically. During flight, the aerial vehicle can hover and transition between a horizontal flight mode and a vertical flight mode using the grid fins.

Abstract translation: 垂直起飞和着陆的微型飞行器包括从转子保护组件沿相反方向延伸的上部机身段和下部机身段。 转子保护组件内的转子在机身段之间旋转。 多个转向叶片从转子下方的转子保护组件延伸。 而且，多个格栅翅片从转向叶片下方的下部机身段径向延伸。 飞行器能够垂直起飞和着陆。 在飞行中，飞行器可以使用网格散热片在水平飞行模式和垂直飞行模式之间悬停和转换。

公开(公告)号：US20030001045A1

公开(公告)日：2003-01-02

申请号：US09895332

申请日：2001-07-02

Applicant: ELSE Ltd.

Inventor： Aharon Yifrach

IPC: B64C003/00

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

公开(公告)号：US5890441A

公开(公告)日：1999-04-06

申请号：US709488

申请日：1996-09-06

Applicant: Johnny Swinson, deceased ,  by Sueanne Walker, executrix ,  Terry J. James

Inventor： Johnny Swinson, deceased ,  by Sueanne Walker, executrix ,  Terry J. James

IPC: B64C29/00 ,  B64C39/02 ,  B64C29/04

CPC classification number: B64C39/024 ,  B64C29/0025 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/187

Abstract: A semiautonomously directed, autonomously controlled, gyroscopically stabilized, horizontal or vertical take off and landing (HOVTOL) flying apparatus employing two vertical lift devices equally and longitudinally spaced from the center of gravity of the apparatus; continuously integrated with a drive train apparatus, optional single or multiple power means; congruously connected thereto horizontal thrust devices. Integral to the vertical lift devices; pitch axis control devices situated at the exhaust orifices therein to vector said devices exhaust slip stream by a autonomous flight control system providing pitch stability. The autonomous flight control system providing continuously all flight control of the apparatus and said system being interfaced to a semiautonomous flight director device providing discrete flight direction function codes thereto. The combined effect of the apparatus is: When the power system rotates; coincident rotation of the drive train causes the vertical lift apparatus and horizontal thrust apparatus to counter rotate at right angles simultaneously providing both vertical lift and gyroscopic roll stability and simultaneously providing both horizontal thrust and gyroscopic yaw stability during flight; the continuous control thereof being accomplished by the autonomous flight control system and the directional steering, and function thereof in four axis effected by the semiautonomous flight director device which provides discrete flight function codes to the autonomous flight control system so as to disallow the initiation of negative flight maneuvers and/or functions providing for the safe unskilled pilot operation of the apparatus or any aircraft employing a autopilot having a autonomous digital flight control system.

Abstract translation: 使用两个垂直升降装置的半自主导向的，自主控制的，陀螺稳定的，水平或垂直的起飞和着陆（HOVTOL）飞行装置，该装置与装置的重心相等地纵向间隔开; 与传动系统设备连续集成，可选单个或多个动力装置; 一致地连接到水平推力装置。 与垂直升降装置成一体; 位于其排气孔处的俯仰轴控制装置通过提供俯仰稳定性的自主飞行控制系统向所述装置排出滑移流。 该自主飞行控制系统连续地提供装置的所有飞行控制，并且所述系统正在连接到半自主飞行指导装置，从而向其提供离散的飞行方向功能代码。 该装置的组合效果是：当电力系统旋转时; 驱动系统的一致旋转导致垂直提升装置和水平推力装置逆时针旋转，同时提供垂直提升和陀螺辊稳定性，同时在飞行期间同时提供水平推力和陀螺仪横摆稳定性; 其连续控制由自主飞行控制系统和定向转向完成，并且其功能由四通道由半自主飞行指导装置实现，该自主飞行控制系统向自主飞行控制系统提供离散飞行功能代码，从而不允许启动负 飞行机动和/或功能，提供设备的安全非技术型飞行员操作或使用具有自主数字飞行控制系统的自动驾驶仪的任何飞行器。

公开(公告)号：US5779190A

公开(公告)日：1998-07-14

申请号：US561929

申请日：1995-11-22

Applicant: James E. Rambo ,  Jerry H. Bowling ,  Robert S. Kincade

Inventor： James E. Rambo ,  Jerry H. Bowling ,  Robert S. Kincade

IPC: B64C39/02 ,  B64C1/16 ,  B64C1/26

CPC classification number: B64C39/024 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/203

Abstract: An unmanned aerial vehicle that includes symmetrical wings, tail section and internal compartments. The wings which include the only control surfaces can be attached to either side of the aircraft. An engine and a payload are non-symmetrically attached modules. Assembly and disassembly is performed with quick release pin and plate latches, quarter turn fasteners and guides that prevent improper assembly. The compartments include quick release hatch covers for the various internal craft compartments.

Abstract translation: 一种包括对称翅膀，尾部和内部舱室的无人驾驶飞行器。 包括唯一控制面的机翼可以安装在飞机的两侧。 发动机和有效载荷是非对称连接的模块。 装配和拆卸使用快速释放销和板闩锁，四分之一转弯紧固件和引导件进行，防止装配错误。 隔间包括各种内部舱室的快速释放舱口盖。

公开(公告)号：US5560568A

公开(公告)日：1996-10-01

申请号：US261901

申请日：1994-06-15

Applicant: Hugh Schmittle

Inventor： Hugh Schmittle

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C3/385 ,  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: Apparatus and method for recovering and arresting an aircraft on a floating platform is disclosed. The aircraft has a fuselage, a wing, and a source of propulsion for propelling the aircraft in flight. During landing approach, an inflatable cushion attached to the fuselage is deployed below the fuselage via inflation. In the inflated condition, a fastening material disposed on a downward facing surface of the cushion is thereby adapted to adhesively contact the floating platform deck so that the forward motion of the aircraft is slowed and arrested. In the preferred embodiment, the fastening material is one of male or female VELCRO.RTM. which is adapted to mate with corresponding VELCRO.RTM. material covering the platform deck.

Abstract translation: 公开了一种用于在浮动平台上恢复和拦截飞行器的装置和方法。 这架飞机有一个机身，一个机翼和一个推进的来源，用于在飞行中推进飞机。 在着陆过程中，通过充气将附着在机身上的充气垫部署在机身的下方。 在充气状态下，设置在缓冲垫的向下的表面上的紧固材料因此适于与浮动平台甲板粘合地接触，使得飞行器的向前运动变慢并且被阻止。 在优选实施例中，紧固材料是男性或女性VELCRO TM之一，其适于与覆盖平台甲板的相应的VELCRO TM材料配合。

公开(公告)号：US5351913A

公开(公告)日：1994-10-04

申请号：US903065

申请日：1992-06-22

Applicant: James P. Cycon ,  Fred W. Kohlhepp ,  Vincent F. Millea

Inventor： James P. Cycon ,  Fred W. Kohlhepp ,  Vincent F. Millea

IPC: B64C27/46 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/02 ,  F02B75/02 ,  B64D35/06

CPC classification number: B64C27/33 ,  B64C27/20 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025

Abstract: One embodiment of a coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a single stage transmission, a transmission housing, and a center hub support structure that are structurally and functionally interactive. The transmission housing includes upper and lower standpipe housings secured in combination with a middle housing. The single stage transmission includes an input pinion gear rotatably mounted in combination with the middle housing, and upper and lower spiral bevel gears rotatably coupled in combination with the input pinion gear to provide counter-rotation thereof. The spiral bevel gears include integral rotor shafts, respectively, rotatably mounted in the standpipe housings. The hub support structure is configured for securement of the middle housing internally in combination therewith, with respective surfaces thereof in abutting engagement so that dynamic loads of the rotors and thermal loads are directly coupled into the hub support structure via the middle housing while bending moments of the rotors are canceled in the middle housing. The hub support structure has radially extending arms for mounting the coaxial transmission/center hub subassembly in fixed coaxial relation to an airframe structure and for coupling the dynamic and thermal loads to the airframe structure. External surfaces of the standpipe housings function as sliding surfaces for linear motion of swashplate subassemblies to minimize the separation between the rotors so that the airframe structure has a compact aerodynamic and structural envelope. The transmission housing is internally configured to provide a splash lubrication subsystem.

Abstract translation: 具有导管的同轴反转转子的转子组件的同轴传动/中心毂子组件的一个实施例包括在结构和功能上相互作用的单级传动装置，变速器壳体和中心轮毂支撑结构。 变速器壳体包括与中间壳体组合固定的上下立管壳体。 单级变速器包括与中间壳体可旋转地安装的输入小齿轮，以及与输入小齿轮可旋转地联接以提供反向转动的上下螺旋锥齿轮。 螺旋锥齿轮分别包括可旋转地安装在立管壳体中的整体转子轴。 轮毂支撑结构构造成用于将中间壳体与内部固定在一起，其相应的表面相互接合，使得转子和热负载的动态载荷通过中间壳体直接联接到轮毂支撑结构中，同时弯曲力矩 转子在中间房屋被取消。 轮毂支撑结构具有径向延伸臂，用于将同轴传动/中心轮毂子组件安装成与机身结构固定的同轴关系，并将动态和热负载耦合到机体结构。 立管外壳的外表面用作滑动表面，用于旋转斜盘组件的直线运动，以最小化转子之间的间隔，使机身结构具有紧凑的空气动力学和结构范围。 变速器壳体内部配置为提供飞溅润滑子系统。

公开(公告)号：US20190016459A1

公开(公告)日：2019-01-17

申请号：US16127640

申请日：2018-09-11

Applicant: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASA

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 ,  B64C25/52 ,  B64C39/02 ,  B64D27/24 ,  B64C5/02 ,  B64D27/02

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.

公开(公告)号：US20180194484A1

公开(公告)日：2018-07-12

申请号：US15866655

申请日：2018-01-10

Applicant: Aurora Flight Sciences Corporation

Inventor： Evangelos Livieratos ,  Riley Griffin ,  Nathan Varney ,  Amanda Dropkin

IPC: B64D27/24 ,  B64D27/04 ,  F02B63/04 ,  F02N11/04 ,  B64C27/08

CPC classification number: B64D27/24 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64D27/04 ,  B64D2027/026 ,  F02B41/04 ,  F02B63/04 ,  F02B75/34 ,  F02B2275/32 ,  F02D13/0269 ,  F02D29/06 ,  F02N11/04 ,  Y02T10/142 ,  Y10S903/903

Abstract: A hybrid-electric aerial vehicle is disclosed comprising: an airframe; a plurality of longitudinal booms extending radially from the airframe; a passively charged internal combustion engine operatively coupled with a fuel tank, a generator operatively coupled with the passively charged internal combustion engine; a battery bank operatively coupled with the generator; and a plurality of motors. The passively charged internal combustion engine has an intake engine valve, an exhaust engine valve, and a combustion chamber, wherein the intake engine valve is delayed to provide an expansion ratio in the combustion chamber that is greater than a compression ratio in the combustion chamber. Each of said plurality of motors may be positioned at a distal end of one of said plurality of longitudinal booms and be operatively coupled with a propeller, wherein the plurality of motors is electrically coupled with the battery bank and the generator.

公开(公告)号：US20180009529A1

公开(公告)日：2018-01-11

申请号：US15693789

申请日：2017-09-01

Applicant: Top Flight Technologies, Inc.

Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

IPC: B64C39/02 ,  B64C27/08 ,  B64D1/08 ,  G05D1/10 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64F3/02 ,  B64D1/22 ,  B64C27/00

CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.

公开(公告)号：US09751625B2

公开(公告)日：2017-09-05

申请号：US15202771

申请日：2016-07-06

Applicant: Top Flight Technologies, Inc.

Inventor： Long N. Phan ,  Sanjay Emani Sarma ,  Cody Miles Wojcik ,  Eli M. Davis ,  Benjamin Arthur Sena ,  Julian Lemus

IPC: B64D41/00 ,  B64C39/02 ,  B64D27/02 ,  B64C27/00 ,  B64C27/08 ,  B64D33/08 ,  B64D27/24 ,  B64D1/08 ,  B64D1/22 ,  B64F3/02 ,  G05D1/10

CPC classification number: B64C39/024 ,  B64C27/001 ,  B64C27/08 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/063 ,  B64C2201/066 ,  B64C2201/108 ,  B64D1/08 ,  B64D1/22 ,  B64D27/02 ,  B64D27/24 ,  B64D33/08 ,  B64D2027/026 ,  B64D2221/00 ,  B64F3/02 ,  G05D1/101 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor.