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    MUFFLER
    71.
    发明申请
    MUFFLER 审中-公开

    公开(公告)号：US20190024548A1

    公开(公告)日：2019-01-24

    申请号：US15736876

    申请日：2016-06-17

    Applicant: ORBITAL AUSTRALIA PTY LTD

    Inventor： Stephen John KARAY ,  Mario Charles MUSCAT ,  Pouria MEHRANI

    IPC: F01N1/08 ,  F01N13/18

    CPC classification number: F01N1/083 ,  B64C39/024 ,  B64C2201/044 ,  F01N1/003 ,  F01N1/023 ,  F01N13/002 ,  F01N13/1833 ,  F01N13/1894

    Abstract: A muffler devised particularly for a small, reciprocating-piston two-stroke internal combustion engine of the type used on unmanned aerial vehicles. The muffler comprises a body incorporating an inlet, an outlet, and a plurality of chambers for exhaust gas flow from the inlet to the outlet. The body is configured to present a compact profile for installation on the engine. The chambers are so configured that adjacent chambers communicate to facilitate exhaust gas flow from the inlet to the outlet via flow passages. The various chambers comprise an inner chamber, an outer chamber, and one or more intervening chambers disposed between the inner and outer chambers. The various chambers are disposed one about another in annular formation. This arrangement creates a long flow path from the inlet to the outlet incorporating various directional changes.

    Hybrid Electric Drive Train For VTOL Drones
    77.
    发明申请
    Hybrid Electric Drive Train For VTOL Drones 审中-公开
    VTOL无人机混合动力传动系

    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。

    Multi-Propulsion Design for Unmanned Aerial Systems
    78.
    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。

    Performing corrective action on unmanned aerial vehicle using one axis of three-axis magnetometer
    79.
    发明授权
    Performing corrective action on unmanned aerial vehicle using one axis of three-axis magnetometer 失效
    使用三轴磁力计一轴对无人机进行校正

    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。

    UNMANNED HELICOPTER
    80.
    发明申请
    UNMANNED HELICOPTER 审中-公开
    无人直升机

    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。

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