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    TAIL SITTER STOP-FOLD AIRCRAFT
    1.
    发明申请
    TAIL SITTER STOP-FOLD AIRCRAFT 有权

    公开(公告)号：US20210253239A1

    公开(公告)日：2021-08-19

    申请号：US16795426

    申请日：2020-02-19

    Applicant: Bell Textron Inc.

    Inventor： Steven Ray Ivans ,  Brent Chadwick Ross ,  Danielle Lynn Moore ,  Berlin Bernard Benfield ,  Jason Paul Hurst

    IPC: B64C29/04 ,  B64C27/50 ,  B64D27/10 ,  B64D35/04 ,  B64C25/32 ,  B64C5/06 ,  B64C5/08 ,  B64C5/04 ,  B64C7/00

    Abstract: Embodiments are directed to a high speed, vertical lift aircraft that has vertical take-off and landing (VTOL) capability and is capable of converting to a forward-flight mode (e.g., prop-mode). The rotors blades can be folded for high speed forward flight propelled by a turbine engine (e.g., jet-mode). The rotor blades on the tail sitter aircraft have a “stop-fold” capability, which means that the rotor blades are stopped in flight and folded back to reduce drag. This allows the tail sitter aircraft to achieve a higher speed than a tilt-rotor aircraft. In some embodiments, the tail sitter aircraft achieves both rotor-borne flight and jet-borne flight by having two separate engines. An additional advantage of the tail-sitter aircraft versus a horizontally oriented fixed engine aircraft is that supplemental jet thrust can be used for take-off if desired.

    Multi-Propulsion Design for Unmanned Aerial Systems
    2.
    发明申请
    Multi-Propulsion Design for Unmanned Aerial Systems 审中-公开
    无人空中系统的多推进设计

    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。

    Superman air motor
    3.
    发明授权
    Superman air motor 失效
    超人气动马达

    公开(公告)号：US06874728B2

    公开(公告)日：2005-04-05

    申请号：US10384045

    申请日：2003-03-06

    Applicant: Kingting Lau

    Inventor： Kingting Lau

    IPC: B64C15/02 ,  B64C29/04 ,  B64C39/02 ,  B64D33/04 ,  B64C39/00

    CPC classification number: B64C39/026 ,  B64C15/02 ,  B64C29/04 ,  B64D33/04

    Abstract: Provided is a disc-type jet turbine engine with controllable and rotational discharge ports at two sides of a discharge chamber, a fuel tank, and an operation lever connected with the discharge ports. The rotor shaft of the jet turbine engine is connected with a start-up electrical motor through a clutch and with a fuel pump through a gearbox. The fuel nozzle of the engine is connected with the fuel tank via the accelerator control valve and the fuel pump. The operation lever controls the clutch. The handle of the operation lever is provided with an electrical switch, a direction controller and an accelerator controller. The switch is electrically connected with the start-up electrical motor, the accelerator controller is connected to control the accelerator control valve, and the direction controller is connected with the discharge ports. Around the combustion chamber is an air-flow guide chamber having an air cooling and heat-insulate layer.

    Abstract translation: 本发明提供一种盘式喷气式涡轮发动机，其在排放室，燃料箱和与排出口连接的操作杆的两侧具有可控和旋转的排出口。 喷气涡轮发动机的转子轴通过离合器与燃料泵通过齿轮箱与起动电动机连接。 发动机的燃油喷嘴通过加速器控制阀和燃油泵与油箱相连。 操作杆控制离合器。 操作杆的手柄设有电气开关，方向控制器和加速器控制器。 开关与起动电动机电连接，加速器控制器连接以控制加速器控制阀，方向控制器与排放口连接。 在燃烧室周围是具有空气冷却和隔热层的气流引导室。

    Horizontal and vertical take off and landing unmanned aerial vehicle
    4.
    发明授权
    Horizontal and vertical take off and landing unmanned aerial vehicle 失效
    水平和垂直起降无人机

    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。

    Disc-type airborne vehicle and radial flow gas turbine engine used therein
    6.
    发明授权
    Disc-type airborne vehicle and radial flow gas turbine engine used therein 失效
    其中使用的盘式机载车辆和径流式燃气涡轮发动机

    公开(公告)号：US4193568A

    公开(公告)日：1980-03-18

    申请号：US842673

    申请日：1977-10-17

    Applicant: Norman L. Heuvel

    Inventor： Norman L. Heuvel

    IPC: B64C39/00 ,  F01D1/28 ,  F01D5/04 ,  B64C29/04 ,  F02C3/14

    CPC classification number: F01D1/28 ,  B64C29/0066 ,  B64C39/001 ,  F01D5/041 ,  F02C3/05

    Abstract: An annular, radial flow gas turbine engine and airborne vehicle utilizing same for jet propulsion. The engine comprises counter-rotating rotors and a compressor section with counter-rotating annular rows of intermeshing compressor blades, an annular combustion section common to both rotors wherein the combustion zone is defined by oppositely rotating rotor walls, and a turbine section made up of annular rows of counter-rotating exhaust turbine blades. No stator blades are present in either the compressor or the turbine sections.The craft comprises a central hub on which the engine rotors rotate on thrust bearings, and air bearings maintain rotor tolerances with respect to each other and to nonrotating shell portions above and below the engine rotors. Air inlet guide vanes leading to the compressor section are also housed in the hub portion of the craft. Exhaust gases emitting from the turbine section are selectively ducted through annularly arranged, downwardly directed lift thrust producing ducts and/or rearwardly directed ducts or vanes for generation of forward propulsion. Directional control during hovering and low speed flight is by selective braking of one or the other of the rotors, and during high speed flight also by selective control of spoiler surfaces arranged in the upper and lower external surfaces of the craft.

    Abstract translation: 一种环形的径向气体燃气涡轮发动机和利用它们用于喷气推进的机载车辆。 发动机包括反向旋转转子和具有相对旋转的环形排相互啮合的压缩机叶片的压缩机部分，两个转子共同的环形燃烧部分，其中燃烧区域由相对旋转的转子壁限定，以及由环形 排列相反的排气涡轮叶片。 没有定子叶片存在于压缩机或涡轮机部分中。工艺包括中心毂，发动机转子在其上推力轴承上旋转，空气轴承相对于彼此保持转子公差，并且保持转子公差在上方和下方 发动机转子。 通向压缩机部分的进气导叶也容纳在工艺的轮毂部分中。 从涡轮部分排出的废气通过环形布置的向下指向的提升推力产生管道和/或向后定向的管道或叶片选择性地导管，以产生向前推进。 悬停和低速飞行期间的定向控制是通过选择性地制动一个或另一个转子，并且在高速飞行期间还可以通过选择性地控制布置在飞行器的上外表面和下外表面中的扰流板表面。

    Modular aircraft with vertical takeoff and landing capability
    10.
    发明授权
    Modular aircraft with vertical takeoff and landing capability 有权

    公开(公告)号：US11447246B2

    公开(公告)日：2022-09-20

    申请号：US16090162

    申请日：2018-05-07

    Applicant: Insitu, Inc.

    Inventor： Peter Josef Kunz ,  David Wayne Goodrich ,  Jacob Scott Allen ,  Matthew Jacob Bartow

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

    Abstract: An aircraft includes a fuselage module and at least two vertical lift rotor modules supporting at least four rotor assemblies. Each rotor assembly is supported by a rotor boom having at least one boom free end and a boom mounting portion. Each rotor assembly has at least one vertical lift rotor mounted on the boom free end. Each boom mounting portion is removably couplable to the fuselage module. The vertical lift rotor modules are configured such that when coupled to the fuselage module, a pair of the rotor assemblies are located on each of laterally opposite sides of the fuselage module, and the rotor assemblies of each pair are respectively located forward of and aft of a wing center portion. A pair of wings are configured to be removably couplable to the wing center portion. The aircraft includes a forward thrust module removably couplable to the fuselage body.

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