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    Rocket-turbine-powered VTOL aircraft
    5.
    发明授权
    Rocket-turbine-powered VTOL aircraft 有权

    公开(公告)号：US11713114B2

    公开(公告)日：2023-08-01

    申请号：US17196643

    申请日：2021-03-09

    Applicant: Textron Innovations Inc.

    Inventor： Troy Cyril Schank

    IPC: B64C29/00 ,  B64D27/02 ,  B64D27/12

    CPC classification number: B64C29/0025 ,  B64D27/023 ,  B64D27/12 ,  B64C2211/00 ,  B64D2027/026

    Abstract: A vertical-takeoff-and-landing (“VTOL”) aircraft including a non-VTOL aircraft equipped for forward takeoff and flight and a modular boom system interoperably coupled to the non-VTOL aircraft. The modular boom system includes a first modular boom and a second modular boom. The first modular boom includes a first rocket-turbine engine. The first modular boom is mounted to a first wing of the non-VTOL aircraft. The second modular boom includes a second rocket-turbine engine. The second modular boom is mounted to a second wing of the non-VTOL aircraft.

    FAN CLUTCH FOR CONVERTIBLE ENGINE
    7.
    发明申请
    FAN CLUTCH FOR CONVERTIBLE ENGINE 有权

    公开(公告)号：US20220194619A1

    公开(公告)日：2022-06-23

    申请号：US17686347

    申请日：2022-03-03

    Applicant: Textron Innovations Inc.

    Inventor： Alan Hisashi Steinert ,  Thomas Dewey Parsons ,  Troy Cyril Schank

    IPC: B64D35/02 ,  B64D27/20 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F04D25/16

    Abstract: Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.

    Lubrication management systems for tiltrotor aircraft
    8.
    发明授权
    Lubrication management systems for tiltrotor aircraft 有权

    公开(公告)号：US11280398B2

    公开(公告)日：2022-03-22

    申请号：US16025147

    申请日：2018-07-02

    Applicant: Textron Innovations Inc.

    Inventor： Thomas Dewey Parsons ,  Troy Cyril Schank

    IPC: F16H57/04 ,  B64C29/00 ,  B64C11/28 ,  B60K11/02

    Abstract: A drive system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The drive system includes an engine to provide rotational energy and a proprotor assembly to receive rotational energy from the engine when the tiltrotor aircraft is in the rotary flight mode. The proprotor assembly is disengaged from the engine in the non rotary flight mode. The drive system includes a proprotor gearbox including one or more gears mechanically interposed between the engine and the proprotor assembly. The proprotor gearbox transfers rotational energy from the engine to the proprotor assembly when the tiltrotor aircraft is in the rotary flight mode. The drive system includes a lubricant operable to reduce friction between the gears and a lubrication management system to affect a temperature of the lubricant to enhance lubrication between the gears in the proprotor gearbox in the rotary flight mode.

    Gimbal lock hook systems for rotorcraft
    10.
    发明授权
    Gimbal lock hook systems for rotorcraft 有权

    公开(公告)号：US10946955B2

    公开(公告)日：2021-03-16

    申请号：US16051343

    申请日：2018-07-31

    Applicant: Textron Innovations Inc.

    Inventor： Troy Cyril Schank ,  Andrew Ryan Maresh ,  Chyau-Song Tzeng

    IPC: B64C27/32 ,  B64C29/00 ,  B64C27/30

    Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The proprotor hub assembly includes a hook receiver. The propulsion assembly includes a gimbal lock positioned about the mast. The gimbal lock includes a locking ring and a gimbal lock hook. The gimbal lock is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. The gimbal lock enables the gimballing degree of freedom in the disengaged position and disables the gimballing degree of freedom in the engaged position. The gimbal lock hook is hooked to the hook receiver in the engaged position to secure the locking ring to the proprotor hub assembly.

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