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    MULTI-DRIVE UNIT PROPULSION SYSTEM FOR AN AIRCRAFT
    5.
    发明公开
    MULTI-DRIVE UNIT PROPULSION SYSTEM FOR AN AIRCRAFT 审中-公开

    公开(公告)号：EP4328139A1

    公开(公告)日：2024-02-28

    申请号：EP23192780.7

    申请日：2023-08-22

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： BERTRAND, Pierre ,  THOMASSIN, Jean

    IPC分类号： B64D35/08 ,  B64D27/24 ,  B64D31/06 ,  B64D35/02

    摘要： A system (20) is provided for an aircraft (22). This aircraft system (20) includes a propulsion system (26), and the propulsion system (26) includes a first thermal engine (56A), a second thermal engine (56B) and a first electric machine (54A). The propulsion system (20) is configured to operate the first thermal engine (56A) and the second thermal engine (56B), without operating the first electric machine (54A), during a first mode of operation to provide aircraft (22) thrust. The propulsion system (26) is configured to operate the first electric machine (54A) and the second thermal engine (56B), without operating the first thermal engine, during a second mode of operation to provide the aircraft thrust.

    HYBRID-ELECTRIC AIRCRAFT PROPULSION SYSTEM AND METHOD FOR OPERATING THE SAME
    8.
    发明公开
    HYBRID-ELECTRIC AIRCRAFT PROPULSION SYSTEM AND METHOD FOR OPERATING THE SAME 审中-公开

    公开(公告)号：EP4227224A1

    公开(公告)日：2023-08-16

    申请号：EP23156395.8

    申请日：2023-02-13

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： FREER, Richard ,  QUILLET, Dominik ,  RANCOURT, David

    IPC分类号： B64D27/02 ,  B64D27/24 ,  B64D31/06 ,  B64D31/14

    摘要： A method of operating a hybrid-electric propulsion system (18) for an aircraft includes: a) providing at least one thermal engine sized to provide sufficient thrust to the aircraft for at least one flight mission independent of a second non-thermal engine source of thrust for the at least one flight mission; b) providing at least one electric motor powered by a non-hydrocarbon-fuel-burning electrical energy source, the at least one electric motor configured to provide thrust to the aircraft for the at least one flight mission; and c) selectively providing thrust during one or more segments of the at least one flight mission using the electric motor.

    AUTOTHROTTLE CONTROL FOR TURBOPROP ENGINES
    9.
    发明公开
    AUTOTHROTTLE CONTROL FOR TURBOPROP ENGINES 审中-公开

    公开(公告)号：EP4219313A1

    公开(公告)日：2023-08-02

    申请号：EP23164482.4

    申请日：2018-02-21

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： LISIO, Carmine ,  MATHESON, Kenneth

    IPC分类号： B64D31/06 ,  F02C9/58 ,  B64C11/30

    摘要： There are described methods and systems for providing an autothrottle mode in a propeller-driven aircraft. A thrust change is obtained corresponding to a difference between an actual thrust and a desired thrust for an engine (110). When greater than a pre-determined threshold, a setting change to one or more control input(s) (201) of the engine (110) is determined. One or more commands is output to cause the setting change of the control input(s) (201).

    REDUCED-ENGINE OPERATION TECHNIQUE FOR ROTORCRAFT
    10.
    发明公开
    REDUCED-ENGINE OPERATION TECHNIQUE FOR ROTORCRAFT 审中-公开

    公开(公告)号：EP4209416A1

    公开(公告)日：2023-07-12

    申请号：EP22214657.3

    申请日：2022-12-19

    申请人： Bell Textron Inc.

    发明人： PARSONS, Thomas Dewey

    IPC分类号： B64C27/06 ,  B64D31/06 ,  B64C27/57 ,  F02C9/42 ,  B64D35/08

    摘要： Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines (224A-224N). The aircraft may have a flight control system (210 coupled to the multiple engines (224A-224N) with a multi-engine interface (224). The flight control system (210) may be configured to shutdown at least one engine of the multiple engines (224A-224N) during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine (224A-224N).