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    Aircraft control method
    1.
    发明授权
    Aircraft control method 有权

    公开(公告)号：US11474540B2

    公开(公告)日：2022-10-18

    申请号：US16907617

    申请日：2020-06-22

    Applicant: ROLLS-ROYCE plc

    Inventor： David Fillingham ,  Marko Bacic

    IPC: G05D1/10 ,  B64C29/00 ,  G08G5/00

    Abstract: A method of automatically determining a flight trajectory of a vertical take-off and landing aircraft having vectorable propulsion can be used to improve flight efficiency. The method includes receiving one or more aircraft flight constraints, inputting the aircraft flight constraints to a trajectory planning algorithm to determine a minimum energy aircraft transition trajectory, and outputting a control schedule to fly the aircraft to along the flight trajectory.

    Method to determine inertia in a shaft system
    2.
    发明授权
    Method to determine inertia in a shaft system 有权
    确定轴系惯性的方法

    公开(公告)号：US09435683B2

    公开(公告)日：2016-09-06

    申请号：US14871013

    申请日：2015-09-30

    Applicant: ROLLS-ROYCE PLC

    Inventor： Marko Bacic

    IPC: G01L3/02 ,  G01H1/00 ,  G01L3/04 ,  G01H13/00 ,  F02C9/28 ,  F02C9/56

    CPC classification number: G01H1/006 ,  F01D5/027 ,  F02C9/28 ,  F02C9/56 ,  F05D2260/80 ,  F05D2270/334 ,  F05D2270/335 ,  G01H13/00 ,  G01L3/04 ,  G01M5/0025

    Abstract: A method to determine inertia of components of a rotating shaft system. The shaft system includes a shaft coupling a turbine to drive the rotation and a load to be driven by the rotation. The method includes steps to: apply a feedback to a forcing input to the shaft system; measure resonant frequency of the shaft; iterate steps 1.a) and 1.b) for different feedbacks; plot resonant frequency squared against gain; and determine inverse of gradient from the plot to give inertia of the turbine. Also a method to determine shaft stiffness using the inertia of the turbine.

    Abstract translation: 确定旋转轴系的部件惯性的方法。 轴系包括联接涡轮以驱动旋转的轴和由旋转驱动的负载。 该方法包括以下步骤：将反馈应用于对轴系统的强制输入; 测量轴的谐振频率; 迭代步骤1.a）和1.b）以获得不同的反馈; 绘制谐振频率对抗增益平方; 并从曲线确定梯度的倒数，给出涡轮机的惯量。 也是使用涡轮机的惯性来确定轴刚度的方法。

    Shaft resonance control
    6.
    发明授权
    Shaft resonance control 有权

    公开(公告)号：US11300059B2

    公开(公告)日：2022-04-12

    申请号：US16598342

    申请日：2019-10-10

    Applicant: ROLLS-ROYCE plc

    Inventor： Marko Bacic

    IPC: F02C9/28 ,  F02C9/48

    Abstract: A method of actively controlling torsional resonance of a rotating shaft of an engine is provided. The shaft has a rotational velocity characterised by a low frequency, rotational velocity term and a high frequency, oscillatory term superimposed on the low frequency term, the oscillatory term being caused by torsional resonance. The method including: measuring the rotational velocity of the shaft; extracting the oscillatory term from the measured rotational velocity; and on the basis of the extracted oscillatory term, applying a torque component to the shaft, the torque component being modulated at the same frequency as the torsional resonance to counteract the torsional resonance.

    Hybrid electric aircraft propulsion system
    7.
    发明授权
    Hybrid electric aircraft propulsion system 有权

    公开(公告)号：US11125104B2

    公开(公告)日：2021-09-21

    申请号：US16391641

    申请日：2019-04-23

    Applicant: ROLLS-ROYCE plc

    Inventor： Marko Bacic

    IPC: F01D15/10 ,  F01D11/24 ,  F02C9/42

    Abstract: The present disclosure concerns control a hybrid electric gas turbine system (300) for an aircraft. The system comprises an electric generator (308) and a gas turbine (309) to form a generator system, an electric motor (303) and a fan (302) to form a propulsor (301), a controller (306) and an electric storage unit (307). After receiving a command for a change in demand for thrust, the controller (306) determines an operational profile that minimises a function comprising a measure of fuel supplied to the gas turbine (309), a transfer of electric power from or to the electric storage unit (307) and a difference between measures of current and demanded thrust over a time period. The controller then operates the electric motor (303), gas turbine (309) and electric storage unit (307) according to the determined operational profile over the time period.

    Gas turbine engine control
    9.
    发明授权
    Gas turbine engine control 有权
    燃气轮机发动机控制

    公开(公告)号：US08996277B2

    公开(公告)日：2015-03-31

    申请号：US13735508

    申请日：2013-01-07

    Applicant: Rolls-Royce PLC

    Inventor： Peter Beecroft ,  Leo Vivian Lewis ,  Marko Bacic

    IPC: G06F19/00 ,  F04D27/02 ,  G05B13/02 ,  F01D11/20 ,  F02C9/00 ,  F02C9/28

    CPC classification number: F02C9/00 ,  F01D11/08 ,  F01D11/20 ,  F02C9/28 ,  F05D2260/80 ,  F05D2260/82

    Abstract: A gas turbine engine control apparatus comprises a controller 34, a memory 36 associated with the controller 34 and inputs 38 for measurement data from an engine. The controller 34 determines the start of a monitoring cycle at 73, receives measurement data at the inputs 38 during the monitoring cycle, manipulates the measurement data to provide an incremental deterioration value representing deterioration occurring within the engine and during the monitoring cycle, and uses the incremental deterioration value at 72 to update a deterioration value 74 stored in the memory 36, and determines the start of a further monitoring cycle.

    Abstract translation: 燃气涡轮发动机控制装置包括控制器34，与控制器34相关联的存储器36和用于来自发动机的测量数据的输入38。 控制器34在73处确定监视周期的开始，在监视循环期间接收输入端38的测量数据，操作测量数据以提供表示发动机内部和监视循环期间的劣化的增量劣化值，并使用 72处的增量劣化值，以更新存储在存储器36中的劣化值74，并确定进一步监视循环的开始。

    Aircraft engine fuel system
    10.
    发明授权
    Aircraft engine fuel system 有权

    公开(公告)号：US12252266B2

    公开(公告)日：2025-03-18

    申请号：US18483106

    申请日：2023-10-09

    Applicant: ROLLS-ROYCE plc

    Inventor： Marko Bacic ,  John Coull

    IPC: B64D37/30 ,  B64D37/34 ,  F02C3/22 ,  F02C7/14 ,  F02C7/22 ,  F02C7/224 ,  F02C9/40

    Abstract: An aircraft propulsion system fuel system comprises a fuel line configured to receive liquid hydrogen fuel from a fuel tank, a vaporizer configured to vaporize liquid hydrogen fuel from the fuel line to generate a supercritical or gaseous fuel, a main fuel pump configured to receive and to pump the gaseous or supercritical fuel from the vaporizer during operation of the propulsion system, and a heater provided downstream in fuel flow to the main fuel pump, and configured to raise the temperature of the gaseous or supercritical fuel to a propulsion system delivery temperature.

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