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    PRECISION POINTING MODE OF AN AIRCRAFT
    2.
    发明申请
    PRECISION POINTING MODE OF AN AIRCRAFT 审中-公开

    公开(公告)号：US20200047881A1

    公开(公告)日：2020-02-13

    申请号：US16057346

    申请日：2018-08-07

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Steven D. Marzella ,  David L. Adams ,  William C. Fell ,  Matthew T. Luszcz

    IPC: B64C27/57 ,  B64D43/02

    Abstract: An aircraft is provided including at least one pilot input and a flight control system n communication with the at least one pilot input. The flight control system is operable in a manual mode and a pointing mode. In the manual mode, a velocity, position, and attitude of the aircraft are controlled manually, and in the pointing mode, at least one of the velocity and position of the aircraft is controlled by the flight control system and at least one of the attitude and heading of the aircraft is controlled manually.

    POWER MANAGEMENT BETWEEN A PROPULSOR AND A COAXIAL ROTOR OF A HELICOPTER
    4.
    发明申请
    POWER MANAGEMENT BETWEEN A PROPULSOR AND A COAXIAL ROTOR OF A HELICOPTER 审中-公开

    公开(公告)号：US20170275011A1

    公开(公告)日：2017-09-28

    申请号：US15504248

    申请日：2015-09-30

    Applicant: SIKORSKY AIRCRAFT CORPORATION

    Inventor： Matthew T. Luszcz

    IPC: B64D31/06 ,  B64D35/00 ,  B64C27/82 ,  B64C11/30 ,  B64C27/10

    Abstract: One aspect is a flight control system for a rotary wing aircraft that includes flight control computer configured to interface with a main rotor system, a translational thrust system, and an engine control system. The flight control computer includes processing circuitry configured to execute control logic. The control logic includes a primary flight control configured to produce flight control commands for the main rotor system and the translational thrust system. Main rotor engine anticipation logic is configured to produce a rotor power demand associated with the main rotor system. Propulsor loads engine anticipation logic is configured to produce an auxiliary propulsor power demand associated with the translational thrust system. The auxiliary propulsor power is combined with the rotor power demand to produce a total power demand anticipation signal for the engine control system.

    ROTOR PHASE CONTROL
    5.
    发明申请
    ROTOR PHASE CONTROL 审中-公开
    转子相位控制

    公开(公告)号：US20170021922A1

    公开(公告)日：2017-01-26

    申请号：US15301142

    申请日：2014-04-02

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Anthony Litwinowicz ,  Kenneth S. Wittmer ,  Matthew T. Luszcz

    IPC: B64C27/57 ,  B64C27/32 ,  B64C27/10 ,  B64C27/72

    CPC classification number: B64C27/57 ,  B64C13/16 ,  B64C27/10 ,  B64C27/32 ,  B64C27/72 ,  B64C2027/7205 ,  Y02T50/34

    Abstract: Embodiments are directed to obtaining data from at least one sensor, processing, by a processor, the data to determine an independent rotor phase lag for each of a plurality of axes associated with a rotorcraft, and issuing, by the processor, at least one command to provide for on-axis moments in accordance with the independent rotor phase lag for each of the axes.

    Abstract translation: 实施例旨在从至少一个传感器获得数据，由处理器处理数据，以确定与旋翼航空器相关联的多个轴中的每一个的独立的转子相位滞后，并且由处理器发出至少一个命令 以根据每个轴的独立转子相位滞后来提供轴上力矩。

    Power management between a propulsor and a coaxial rotor of a helicopter
    6.
    发明授权
    Power management between a propulsor and a coaxial rotor of a helicopter 有权

    公开(公告)号：US11377222B2

    公开(公告)日：2022-07-05

    申请号：US16530264

    申请日：2019-08-02

    Applicant: SIKORSKY AIRCRAFT CORPORATION

    Inventor： Matthew T. Luszcz

    IPC: B64D31/06 ,  B64C27/22 ,  B64C11/30 ,  B64C27/10 ,  B64C27/82 ,  B64D35/00 ,  B64C27/57

    Abstract: One aspect is a flight control system for a rotary wing aircraft that includes flight control computer configured to interface with a main rotor system, a translational thrust system, and an engine control system. The flight control computer includes processing circuitry configured to execute control logic. The control logic includes a primary flight control configured to produce flight control commands for the main rotor system and the translational thrust system. A main engine anticipation logic is configured to produce a rotor power demand associated with the main rotor system. A propulsor loads engine anticipation logic is configured to produce an auxiliary propulsor power demand associated with the translational thrust system. The flight control computer providing the engine control system with a total power demand anticipation signal based on a combination of the rotor power demand and the auxiliary propulsor power demand.

    POWER MANAGEMENT BETWEEN A PROPULSOR AND A COAXIAL ROTOR OF A HELICOPTER
    7.
    发明申请
    POWER MANAGEMENT BETWEEN A PROPULSOR AND A COAXIAL ROTOR OF A HELICOPTER 审中-公开

    公开(公告)号：US20190352014A1

    公开(公告)日：2019-11-21

    申请号：US16530264

    申请日：2019-08-02

    Applicant: SIKORSKY AIRCRAFT CORPORATION

    Inventor： Matthew T. Luszcz

    IPC: B64D31/06 ,  B64C27/82 ,  B64C11/30 ,  B64D35/00 ,  B64C27/57 ,  B64C27/10

    Abstract: One aspect is a flight control system for a rotary wing aircraft that includes flight control computer configured to interface with a main rotor system, a translational thrust system, and an engine control system. The flight control computer includes processing circuitry configured to execute control logic. The control logic includes a primary flight control configured to produce flight control commands for the main rotor system and the translational thrust system. A main engine anticipation logic is configured to produce a rotor power demand associated with the main rotor system. A propulsor loads engine anticipation logic is configured to produce an auxiliary propulsor power demand associated with the translational thrust system. The flight control computer providing the engine control system with a total power demand anticipation signal based on a combination of the rotor power demand and the auxiliary propulsor power demand.

    ELEVATOR AND RUDDER CONTROL OF A ROTORCRAFT
    8.
    发明申请
    ELEVATOR AND RUDDER CONTROL OF A ROTORCRAFT 审中-公开

    公开(公告)号：US20190017569A1

    公开(公告)日：2019-01-17

    申请号：US16010615

    申请日：2018-06-18

    Applicant: Sikorsky Aircraft Corporation

    Inventor： Erez Eller ,  Matthew T. Luszcz ,  William J. Eadie

    IPC: F16F15/02 ,  B64C27/12

    Abstract: An aircraft includes an airframe having an empennage, a counter rotating, coaxial main rotor assembly located at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the empennage and providing translational thrust to the airframe. At least two control surfaces located at the empennage are independently operable via commands from one or more flight control computers. A method of operating an aircraft includes transmitting a first signal from one or more flight control computers to a first control surface located at a first lateral side of a translational thrust system, and actuating the first control surface to a first position via the first signal. A second signal is transmitted to a second control surface located at a second lateral side opposite the first lateral side, and the second control surface is actuated to a second position via the second signal.

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