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    INTERCONNECT DRIVE SYSTEM
    12.
    发明公开
    INTERCONNECT DRIVE SYSTEM 有权

    公开(公告)号：EP3395680A1

    公开(公告)日：2018-10-31

    申请号：EP17204970.2

    申请日：2017-12-01

    Applicant: Bell Helicopter Textron Inc.

    Inventor： ELLIOTT, David ,  STAMPS, Frank Bradley ,  COLLINS, Bobby

    IPC: B64C11/50 ,  B64C29/00 ,  B64D35/08 ,  B64D35/04

    CPC classification number: B64C29/0033 ,  B64C11/50 ,  B64D35/04 ,  B64D35/08

    Abstract: An interconnect drive system for an aircraft (11) has a driveline (43) and clutch control system. The driveline (43) comprises a shaft (45, 47, 49) for each propulsion assembly, each shaft for transferring torque to and from the associated propulsion assembly (25, 27), and a clutch (53) operably coupling the shafts and configured for selective engagement. The clutch is capable of transferring a first amount of torque between the shafts while engaged and a second amount of torque between the shafts while disengaged. The system also has a clutch control system (57), comprising a computer (59) operably connected to the clutch (53) for controlling operation of the clutch and sensors (61) for sensing torque applied to the driveline (43), output from the sensors being communicated to the computer. The computer commands operation of the clutch in response to the output from the sensors, the clutch being commanded to disengage to relieve a transient torque imbalance in the driveline.

    AIRCRAFT HAVING ROTOR-TO-WING CONVERSION CAPABILITIES
    14.
    发明授权
    AIRCRAFT HAVING ROTOR-TO-WING CONVERSION CAPABILITIES 有权

    公开(公告)号：EP3290338B1

    公开(公告)日：2018-09-12

    申请号：EP17163295.3

    申请日：2017-03-28

    Applicant: Bell Helicopter Textron Inc.

    Inventor： ROBERTSON, Daniel Bryan ,  GRONINGA, Kirk Landon ,  STAMPS, Frank Bradley

    IPC: B64C29/02

    CPC classification number: B64C29/02 ,  B64C3/56 ,  B64C25/52 ,  B64C27/24 ,  B64C27/50 ,  B64C27/54

    Abstract: A tail sitter aircraft (10) includes a fuselage (12) having a forward portion (14) and an aft portion (16). The forward portion (14) of the fuselage (12) includes first and second rotor stations (18, 20). A first rotor assembly (22) is positioned proximate the first rotor station (18). A second rotor assembly (24) is positioned proximate the second rotor station (20). A tailboom assembly (26) extends from the aft portion (16) of the fuselage (12). The tailboom assembly (26) includes a plurality of landing members (28). In a vertical takeoff and landing mode of the aircraft (10), the first and second rotor assemblies (22, 24) rotate about the fuselage (12) to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly (22) rotates about the fuselage (12) to provide forward thrust and the second rotor assembly (24) is non-rotatable about the fuselage (12) forming wings to provide lift.

    ROTOR SEQUENCING FOR DUAL ROTOR AIRCRAFT
    15.
    发明公开
    ROTOR SEQUENCING FOR DUAL ROTOR AIRCRAFT 有权
    双旋翼飞机的旋转序列

    公开(公告)号：EP3318489A1

    公开(公告)日：2018-05-09

    申请号：EP17193869.9

    申请日：2017-09-28

    Applicant: Bell Helicopter Textron Inc.

    Inventor： STAMPS, Frank Bradley ,  GONZALEZ, Eric Ricardo

    IPC: B64C27/10 ,  B64C11/28

    CPC classification number: B64C27/605 ,  B64C11/28 ,  B64C27/10 ,  B64C27/12 ,  B64C27/50 ,  B64C39/024

    Abstract: An aircraft (10) has a fuselage (28), a first rotor assembly (36) having a first rotor hub (38) and first rotor blades (40a, 40b, 40c) pivotably coupled to the first rotor hub (38) and a second rotor assembly (56) having a second rotor hub (58) and second rotor blades (60a, 60b, 60c) pivotably coupled to the second rotor hub (58). The first (40a, 40b, 40c) and second (60a, 60b, 60c) rotor blades have deployed configurations extending generally radially from the fuselage (28) and stowed configurations extending generally parallel with the fuselage (28). A sequencing cam (90), positioned between the first (38) and second (58) rotor hubs, is coupled to the second rotor blades (60a, 60b, 60c). The sequencing cam (90) has a retracted orientation when the second rotor blades (60a, 60b, 60c) are in the stowed configuration and an extended orientation when the second rotor blades (60a, 60b, 60c) are in the deployed configuration in which the sequencing cam (90) props support arms (42a, 42b, 42c) of the first rotor blades (40a, 40b, 40c) preventing transition of the first rotor blades (40a, 40b, 40c) from the deployed configuration to the stowed configuration.

    Abstract translation: 一种飞机（10）具有机身（28），具有第一转子轮毂（38）和可枢转地联接到第一转子轮毂（38）的第一转子叶片（40a，40b，40c）的第一转子组件（36） 具有第二转子轮毂58的第二转子组件56以及可枢转地联接到第二转子轮毂58的第二转子叶片60a，60b，60c。 第一（40a，40b，40c）和第二（60a，60b，60c）转子叶片具有从机身（28）大致径向延伸的展开构型和大致平行于机身（28）延伸的收起构型。 定位在第一转子毂（38）和第二转子毂（58）之间的定序凸轮（90）联接到第二转子叶片（60a，60b，60c）。 当第二转子叶片（60a，60b，60c）处于收起构型时，定序凸轮（90）具有缩回取向，而当第二转子叶片（60a，60b，60c）处于展开构型时，定向凸轮 定序凸轮90支撑第一转子叶片40a，40b，40c的支撑臂42a，42b，42c，以防止第一转子叶片40a，40b，40c从展开结构转换到收起结构 。

    HELICOPTER TAIL ROTOR BLADE WITH COMPOSITE YOKE FITTING
    16.
    发明公开
    HELICOPTER TAIL ROTOR BLADE WITH COMPOSITE YOKE FITTING 有权
    HECKROTORBLATTANORDUNG旋翼机及其制造方法

    公开(公告)号：EP3072814A1

    公开(公告)日：2016-09-28

    申请号：EP15188195.0

    申请日：2015-10-02

    Applicant: Bell Helicopter Textron Inc.

    Inventor： HALDEMAN, Andrew ,  STAMPS, Frank Bradley ,  SUTTON, Drew

    IPC: B64C27/48 ,  B64C27/473

    CPC classification number: B64C27/46 ,  B64C27/48 ,  B64C2027/4736

    Abstract: A rotor blade assembly includes a rotor blade (504) comprising an inboard end (506) and an outboard end (508). A composite yoke fitting (502) made from a composite material is attached to the rotor blade (504). The composite yoke fitting (502) includes an outboard portion (510) inserted into the inboard end (506) of the rotor blade (504), an inboard portion (512), and a flexure region (514) about which the rotor blade (504) is configured to flex. The inboard portion (512) and the flexure region (514) are outside the rotor blade (504).

    HUB MOUNTED VIBRATION REDUCTION SYSTEM FOR COAXIAL ROTOR SYSTEMS
    19.
    发明公开
    HUB MOUNTED VIBRATION REDUCTION SYSTEM FOR COAXIAL ROTOR SYSTEMS 审中-公开

    公开(公告)号：EP3594116A1

    公开(公告)日：2020-01-15

    申请号：EP18195829.9

    申请日：2018-09-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： STAMPS, Frank Bradley ,  GONZALEZ, Eric ,  SMITH, Michael R

    IPC: B64C27/00 ,  B64C27/10

    Abstract: Systems and methods include providing a coaxial helicopter (100) with a main rotor system (110) having an upper rotor system (112), a coaxial counter-rotating lower rotor system (116), and a rotor mast assembly (120) having an upper rotor mast (122) and a coaxial counter-rotating lower rotor mast (124). The upper rotor system (112) and an associated upper vibration reduction system (130) are coupled to the upper rotor mast (122). The upper vibration reduction system (130) provides in-plane vibration control and reduction to the upper rotor system (112). The lower rotor system (116) and an associated lower vibration reduction system (140) are coupled to the lower rotor mast (124). The lower vibration reduction system (140) provides in-plane vibration control and reduction to the lower rotor system (116). A third vibration reduction system (800) is coupled to the rotor mast assembly (120) and cooperates with the upper (130) and lower (140) vibration reduction systems to provide total in-plane vibration control and reduction to the main rotor system (110).

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