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    SUSTAINED OVER-THE-HORIZON VERTICAL TAKEOFF AND LANDING SENSING SYSTEM
    42.
    发明申请
    SUSTAINED OVER-THE-HORIZON VERTICAL TAKEOFF AND LANDING SENSING SYSTEM 有权
    可持续发展的垂直起落架和陆地传感系统

    公开(公告)号：US20140316608A1

    公开(公告)日：2014-10-23

    申请号：US13866489

    申请日：2013-04-19

    Applicant: SIKORSKY AIRCRAFT CORPORATION

    Inventor： Mark R. Alber ,  Timothy Fred Lauder ,  Jonathan Hartman ,  Bryan Clark Holasek

    IPC: B64C19/00 ,  B64C29/00 ,  B64D47/00 ,  B64C39/02

    CPC classification number: B64C19/00 ,  B64C29/00 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/123 ,  B64C2201/148 ,  B64D47/00

    Abstract: An electrically powered of the vertical takeoff and landing aircraft configured for use with a tether station having a continuous power source is provided including at least one rotor system. The vertical takeoff and landing aircraft additionally has an autonomous flight control system coupled to the continuous power source. The autonomous flight control system is configured to operate an electrical motor coupled to the at least one rotor system such that the vertical takeoff and landing aircraft continuously hovers above the tether station in a relative position. The vertical takeoff and landing aircraft also includes a detection system for detecting objects at a distance from the vertical takeoff and landing aircraft.

    Abstract translation: 提供了一种配置成与具有连续动力源的系绳站一起使用的垂直起飞和着陆飞机的电力供应器，其包括至少一个转子系统。 垂直起飞和着陆飞机还具有耦合到连续电源的自主飞行控制系统。 自主飞行控制系统被配置为操作耦合到至少一个转子系统的电动机，使得垂直起飞和着陆飞机在相对位置连续地悬挂在系绳站上方。 垂直起降飞机还包括一个检测系统，用于检测与垂直起飞和着陆飞机相距一定距离处的物体。

    Drive system arrangement for rotorcraft
    43.
    发明授权
    Drive system arrangement for rotorcraft 有权

    公开(公告)号：US11148822B2

    公开(公告)日：2021-10-19

    申请号：US15758056

    申请日：2016-08-25

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Mark R. Alber

    IPC: B64D35/08 ,  B64C27/14 ,  B64D35/04 ,  B64C27/82 ,  B64D35/02 ,  F02C6/20

    Abstract: A drive system for a rotorcraft includes at least one engine, the engine including a compressor section, and a turbine section positioned rearward from the compressor section. A main rotor input shaft extends from a rotor power turbine of the turbine section and is connectable to a main rotor assembly of the rotorcraft to transfer rotational energy from the rotor power turbine to the main rotor assembly. An auxiliary input shaft extends from an auxiliary power turbine of the turbine section and is connectible to an auxiliary rotor assembly of the rotorcraft to transfer rotational energy from the auxiliary power turbine to the auxiliary rotor assembly.

    Blade fold system using flap hinge
    44.
    发明授权
    Blade fold system using flap hinge 有权

    公开(公告)号：US10933992B2

    公开(公告)日：2021-03-02

    申请号：US15336195

    申请日：2016-10-27

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Bryan Kenneth Baskin ,  Frank P. D'Anna ,  Mark R. Alber

    IPC: B64C29/02 ,  B64C11/28 ,  B64C27/50

    Abstract: A rotor system of a tail-sitter aerial vehicle configured to rotate about an axis of rotation is provided including a rotor hub which rotates about the axis of rotation and at least one rotor blade operably coupled to the rotor hub. The at least one rotor blade is configured to rotate about a folding axis between an extended position where the at least one rotor blade is substantially within a plane perpendicular to the axis of rotation and a stowed position where the rotor blade is arranged out of the plane of at an angle less than ninety degrees to the axis of rotation.

    Aircraft with overlapped rotors
    45.
    发明授权
    Aircraft with overlapped rotors 有权

    公开(公告)号：US10589854B2

    公开(公告)日：2020-03-17

    申请号：US15285207

    申请日：2016-10-04

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Mark R. Alber ,  Jeffrey Parkhurst ,  Charles Gayagoy

    IPC: B64C29/00 ,  B64C3/16 ,  B64C3/32 ,  B64D27/12

    Abstract: An aircraft is provided and includes a fuselage from which a tilt-wing respectively extends, first prop-rotors, which are formed to define first rotor disks and which are respectively disposed on first portions of each side of the tilt-wing, second prop-rotors, which are formed to define second rotor disks and which are respectively disposed on second portions of each side of the tilt-wing such that the corresponding pairs of first and second rotor disks overlap, and a drive shaft system. The drive shaft system is configured to synchronize respective operations of the first and second prop-rotors.

    SYSTEMS AND METHODS FOR AIRCRAFT BALANCE
    49.
    发明申请
    SYSTEMS AND METHODS FOR AIRCRAFT BALANCE 审中-公开

    公开(公告)号：US20180148161A1

    公开(公告)日：2018-05-31

    申请号：US15364166

    申请日：2016-11-29

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Jeffery Parkhurst ,  Mark R. Alber

    IPC: B64C17/00 ,  B64C29/02

    CPC classification number: B64C29/02 ,  B64D1/22

    Abstract: An adjustable cable attachment system for a VTOL aircraft includes a VTOL airframe. A winch is operatively connected to an underside of the airframe with the aircraft in a horizontal flight mode. An adjustable cable is operatively connected to the winch to adjustably relocate a slung load with respect to the center of gravity of the aircraft to balance the aircraft. A fixed cable is operatively connected to the underside of the airframe with the aircraft in the horizontal flight mode.

    PIVOT SYSTEMS FOR TILTWING AIRCRAFT
    50.
    发明申请
    PIVOT SYSTEMS FOR TILTWING AIRCRAFT 审中-公开

    公开(公告)号：US20180086446A1

    公开(公告)日：2018-03-29

    申请号：US15274040

    申请日：2016-09-23

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Mark R. Alber

    IPC: B64C29/00 ,  B64C3/38

    CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C5/02 ,  B64C39/04 ,  B64D35/08

    Abstract: A tiltwing aircraft includes a fuselage, an engine mounted stationary relative to the fuselage, and an opposed pair of wings. The wings are separated from each other with the fuselage therebetween, each wing independently mounted to the fuselage by a respective pivot system for rotation relative to the fuselage. An opposed pair of rotor assemblies is included, each operatively connected to a respective one of the wings for common rotation with the respective wing back and forth between a first position predominantly for lift to a second position predominantly for thrust.

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