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    Horizontal and vertical take off and landing unmanned aerial vehicle
    211.
    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。

    Coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors
    212.
    发明授权
    Coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
    用于转子组件的同轴传动/中心毂子组件，其具有导管的，同轴的反向转动的转子

    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。

    METHOD AND SYSTEM FOR DETECTION AND RECOVERY OF BLOCKED AIR FLOW
    214.
    发明公开
    METHOD AND SYSTEM FOR DETECTION AND RECOVERY OF BLOCKED AIR FLOW 审中-公开

    公开(公告)号：US20230373622A1

    公开(公告)日：2023-11-23

    申请号：US17751221

    申请日：2022-05-23

    Applicant: Johnson Controls Tyco IP Holdings LLP

    Inventor： Jason M. Ouellette ,  Glenn HOLTON

    IPC: B64C39/02 ,  B64C11/46

    CPC classification number: B64C39/024 ,  B64C11/46 ,  B64C2201/162 ,  B64C2201/108

    Abstract: A method for detection of air flow disruption includes monitoring air flow generated by an air propulsion system to detect one or more air flow anomalies indicating potentially blocked air flow. In response to detecting the one or more air flow anomalies, the airflow generated by the air propulsion system may be automatically reversed or temporarily stopped. A determination may be made whether the one or more detected air flow anomalies are resolved by the reversed or stopped air flow. The airflow generated by the air propulsion system prior to the detection of the one or more air flow anomalies may be resumed, in response to determining that the one or more air flow anomalies are resolved.

    Multi-Modal Mobility Unmanned Vehicle
    215.
    发明公开
    Multi-Modal Mobility Unmanned Vehicle 审中-公开

    公开(公告)号：US20230150660A1

    公开(公告)日：2023-05-18

    申请号：US18055757

    申请日：2022-11-15

    Applicant: California Institute of Technology

    Inventor： Alireza Ramezani ,  Morteza Gharib

    IPC: B64C37/00 ,  B64C39/02

    CPC classification number: B64C37/00 ,  B64C39/024 ,  B64C2201/162

    Abstract: In some embodiments, a multi-modal robot can be capable of aerial mobility and ground mobility, and can switch between configuration. The multi-modal robot can include a chassis, and a leg attached to the chassis. The leg can include a frontal hip joint. The frontal hip joint can rotate around a frontal hip axis of rotation. The frontal hip axis of rotation can be parallel to a longitudinal axis of the chassis. The leg can further include a sagittal hip joint, wherein the sagittal hip joint is coupled to the first distal end of a first link. The sagittal hip joint can rotate around a sagittal hip axis of rotation. The leg can include a wheel. The wheel can be configured to rotate around a wheel axis of rotation. The leg can further include a propeller. The propeller can be co-axial with the wheel.

    MOTOR FOR DRONE AND DRONE INCLUDING SAME
    216.
    发明申请
    MOTOR FOR DRONE AND DRONE INCLUDING SAME 审中-公开

    公开(公告)号：US20190252938A1

    公开(公告)日：2019-08-15

    申请号：US16317403

    申请日：2017-07-12

    Applicant: LG INNOTEK CO., LTD.

    Inventor： Young Dae PARK

    IPC: H02K5/10 ,  H02K5/20 ,  F04D25/08 ,  B64C39/02

    CPC classification number: H02K5/10 ,  B64C25/32 ,  B64C27/08 ,  B64C27/12 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/162 ,  F04D25/08 ,  H02K1/27 ,  H02K5/20 ,  H02K7/00 ,  H02K7/14 ,  H02K9/16

    Abstract: The present invention provides a motor for a drone, comprising: a rotary shaft; a stator including a hole into which the rotary shaft is inserted; and a rotor arranged on the outer side of the stator, wherein the rotor comprises: a cover part coupled to the rotary shaft so as to cover the upper portion of the stator; a body part for covering a side portion of the stator; and a magnet coupled to the inner circumferential surface of the body part, wherein the cover part comprises: a propeller coupling part including a hole through which the rotary shaft penetrates; an upper surface part connected to the body part; a connecting part for connecting the propeller coupling part and the upper surface part; and a plurality of blades arranged in the radial direction from the lateral surface of the propeller coupling part and formed so as to be spaced apart from the upper surface part. Therefore, the present invention provides the advantageous effects of preventing water or foreign material from permeating into the motor while ensuring an air passage for heat dissipation.

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