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    AIRCRAFT HAVING SINGLE-AXIS GIMBAL MOUNTED PROPULSION SYSTEMS
    1.
    发明公开
    AIRCRAFT HAVING SINGLE-AXIS GIMBAL MOUNTED PROPULSION SYSTEMS 审中-公开

    公开(公告)号：EP3492372A1

    公开(公告)日：2019-06-05

    申请号：EP18179967.7

    申请日：2018-06-26

    Applicant: Bell Helicopter Textron Inc.

    Inventor： OLDROYD, Paul K ,  McCULLOUGH, John Richard

    IPC: B64C11/32 ,  B64C11/46 ,  B64C29/02 ,  B64C29/00

    Abstract: An aircraft (10; 100; 200) has an airframe (12) with a distributed thrust array attached thereto that includes a plurality of propulsion assemblies (26a-d; 102a-d; 202a-d; 302) each of which is independently controlled by a flight control system (32; 114; 214). Each propulsion assembly (26a-d; 201a-d; 302) includes a housing (28a-d; 126; 226) with a gimbal (106a-d; 206a-d) coupled thereto and operable to tilt about a single axis. A propulsion system (36a-d; 112a-d) is coupled to and operable to tilt with the gimbal (106a-d; 206a-d). The propulsion system (36a-d; 112a-d; 212a-d) includes an electric motor (136; 236) having an output drive (138; 238) and a rotor assembly (34a-d; 306) having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector with a magnitude in the longitudinal direction. Actuation of each gimbal (106a-d; 206a-d) is operable to tilt the respective propulsion system (36a-d; 112a-d; 212a-d) relative to the airframe (12) in the longitudinal direction to change the rotational plane of the respective rotor assembly (34a-d; 306) relative to the airframe, thereby controlling the magnitude of the respective thrust vector in the longitudinal direction.

    METHOD OF CONSTRUCTING A THERMOPLASTIC COMPONENT
    2.
    发明公开
    METHOD OF CONSTRUCTING A THERMOPLASTIC COMPONENT 审中-公开

    公开(公告)号：EP3498459A1

    公开(公告)日：2019-06-19

    申请号：EP18155541.8

    申请日：2018-02-07

    Applicant: Bell Helicopter Textron Inc.

    Inventor： SUTTON, Drew Alan ,  OLDROYD, Paul K

    IPC: B29C65/00 ,  B29C65/02 ,  B29C65/04 ,  B29C65/06 ,  B32B7/04

    Abstract: Systems and methods of constructing a thermoplastic component (120) include joining a thermoplastic skin (102) to a thermoplastic core (104) by introducing heat (108) at an interface (103, 105) of each of the thermoplastic skin (102) and the thermoplastic core (104) to at least partially melt the thermoplastic skin (102) to a thermoplastic core (104) at the interfaces(103, 105), applying pressure to at least one of the thermoplastic skin (102) and the thermoplastic core (104) to sandwich the elements, and cooling the interfaces (103, 105) below the melting point of each of the thermoplastic skin (102) and the thermoplastic core (104) to consolidate the thermoplastic skin (102) and the thermoplastic core (104) into a unitary thermoplastic component (120). An optional thermoplastic film (310) may be disposed between the thermoplastic skin (102) and the thermoplastic core (104). The thermoplastic film (310) may be joined to the thermoplastic core (104) to form an intermediate thermoplastic component (519) prior to joining the thermoplastic skin (102) to the intermediate component (519).

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