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.

公开(公告)号：US20170057630A1

公开(公告)日：2017-03-02

申请号：US15119812

申请日：2015-02-17

Applicant: IAT 21 INNOVATIVE AERONAUTICS TECHNOLOGIES GMBH

Inventor： Meinhard Schwaiger

IPC: B64C29/00 ,  B64C3/56 ,  B64C27/02 ,  B64C39/02 ,  B64D27/04 ,  B64D27/24 ,  B64C3/38 ,  B64C27/20

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/56 ,  B64C27/026 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/04 ,  B64D27/24 ,  B64D2027/026 ,  B64D2211/00

Abstract: The invention relates to an aircraft comprising a fuselage (1), a plurality of propeller units (3) that can pivot in relation to the fuselage (1), and wings (5) that can pivot at least partially in relation to the fuselage (1) and independently of the propeller units (3).

Abstract translation: 本发明涉及一种飞机，其包括机身（1），可相对于机身（1）枢转的多个螺旋桨单元（3）和能够相对于机身至少部分地枢转的翼（5） 1）并且独立于螺旋桨单元（3）。

公开(公告)号：US09527597B1

公开(公告)日：2016-12-27

申请号：US14153721

申请日：2014-01-13

Applicant: Jaime Sada ,  David Alejandro Arrellano Escarpita

Inventor： Jaime Sada ,  David Alejandro Arrellano Escarpita

IPC: B64D27/08 ,  B64C39/02

CPC classification number: B64D27/08 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64D37/04

Abstract: An Unmanned Aerial Vehicle (UAV) for use in military and civilian functions, including a UAV being optimized by utilizing a front and a rearmost engine positioning in addition to an engine operating system for maximum fuel efficiency and performance.

Abstract translation: 用于军事和民用功能的无人飞行器（UAV），包括通过利用前置和后期发动机定位优化的UAV，除了发动机操作系统之外，还可以最大限度地提高燃油效率和性能。

公开(公告)号：US20160311544A1

公开(公告)日：2016-10-27

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: B64D27/24 ,  B64D33/08 ,  B64C27/00 ,  B64C39/02 ,  B64C27/08

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.

Abstract translation: 一种包括至少一个转子电动机的无人驾驶飞行器。 转子电机由微型混合发电系统供电。 微型混合发电机系统包括被配置为向至少一个转子电动机提供电力的可再充电电池，被配置为产生机械功率的小型发动机，耦合到小型发动机的发电机电动机，并且被配置为使用由 小型发动机，桥式整流器，被配置为将由发电电动机产生的交流电力转换为直流电力，并将DC电力提供给可再充电电池和至少一个转子电动机中的一个或两者;以及电子控制单元， 所述小型发动机的节气门至少部分地基于至少一个负载的功率需求，所述至少一个负载包括所述至少一个转子电动机。

公开(公告)号：US20160244158A1

公开(公告)日：2016-08-25

申请号：US14121001

申请日：2014-08-13

Applicant: USA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINSTRATION

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 ,  B64C3/40 ,  B64C9/14 ,  B64C39/02 ,  B64C11/50 ,  B64C25/32 ,  B64C3/38 ,  B64D27/24 ,  B64D27/26

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为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推进系统。