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    DUAL ROTOR PROPULSION SYSTEMS FOR TILTROTOR AIRCRAFT
    2.
    发明公开
    DUAL ROTOR PROPULSION SYSTEMS FOR TILTROTOR AIRCRAFT 审中-公开

    公开(公告)号：EP3495260A1

    公开(公告)日：2019-06-12

    申请号：EP18208692.6

    申请日：2018-11-27

    Applicant: Bell Helicopter Textron Inc.

    Inventor： BRAND, Albert G. ,  ISAAC, Mark Loring ,  STAMPS, Frank Bradley ,  MUELLER, Russell Lee

    IPC: B64C11/48 ,  B64C29/00 ,  B64C27/28

    Abstract: A dual rotor propulsion system (200, 300) for a tiltrotor aircraft (10, 100) having VTOL and forward flight modes. The dual rotor propulsion system (200, 300) includes an engine (202, 302) operable to provide an input torque to a transmission (206, 306) that, responsive thereto, generates an output torque. A first output shaft (214a, 314a) is coupled to the transmission (206, 306) and is operable to receive a first portion of the output torque. A first rotor assembly (216a, 316a) is coupled to and rotatable with the first output shaft (214a, 314a). A second output shaft (214b, 314b) is coupled to the transmission (206, 306) and is operable to receive a second portion of the output torque. A second rotor assembly (216b, 316b) is coupled to and rotatable with the second output shaft (214b, 314b). In operation, the first and second rotor assemblies (216a, 316a, 216b, 316b) rotate coaxially, the first rotor assembly (216a, 316a) is a different diameter than the second rotor assembly (216b, 316b) and the first rotor assembly (216a, 216b) is stoppable and foldable in the forward flight mode.

    ROTOR HUB ASSEMBLY WITH UNIVERSAL JOINT
    5.
    发明公开
    ROTOR HUB ASSEMBLY WITH UNIVERSAL JOINT 审中-公开

    公开(公告)号：EP3434588A1

    公开(公告)日：2019-01-30

    申请号：EP18180551.6

    申请日：2018-06-28

    Applicant: Bell Helicopter Textron Inc.

    Inventor： RAUBER, Richard E. ,  STAMPS, Frank Bradley

    IPC: B64C27/41

    Abstract: A rotor hub assembly (101; 201) that includes a yoke (111; 211) configured to attach blades (107) thereto, a universal joint (109; 209) configured to attach to, and transmit forces between, a mast (105; 205) and the yoke (111; 211), and an elastomeric member (265) configured to attenuate vibrations transmitted from the universal joint (109; 209) to the mast (105; 205).

    ARTICULATED ROTOR SYSTEMS WITH PITCH INDEPENDENT DAMPING
    8.
    发明公开
    ARTICULATED ROTOR SYSTEMS WITH PITCH INDEPENDENT DAMPING 审中-公开

    公开(公告)号：EP3421361A1

    公开(公告)日：2019-01-02

    申请号：EP18167032.4

    申请日：2018-04-12

    Applicant: Bell Helicopter Textron Inc.

    Inventor： PARHAM, Jr., Thomas Clement ,  MILLER, Gary ,  STAMPS, Frank Bradley ,  CHOI, Jouyoung Jason

    IPC: B64C27/35 ,  B64C29/00 ,  B64C27/635 ,  B64C27/51

    Abstract: A proprotor system (32a, 32b) operable for use on a tiltrotor aircraft (10) having a helicopter flight mode and an airplane flight mode. The proprotor system (32a, 32b) includes a rotor hub (102) and a plurality of proprotor blades (34) coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis (128), blade flap about a flapping axis (130) and lead-lag about a lead-lag axis (132). Each of a plurality of spherical bearings couples one of the proprotor blades (34) with the rotor hub (102) . In addition, each of a plurality of lead-lag dampers (134) couples one of the proprotor blades (34) with the rotor hub (102), wherein each lead-lag damper is aligned with the pitch change axis (128) of the respective proprotor blade, thereby providing pitch independent lead-lag damping.

    EXTENDED RANGE QUAD TILTROTOR AIRCRAFT
    10.
    发明公开
    EXTENDED RANGE QUAD TILTROTOR AIRCRAFT 审中-公开

    公开(公告)号：EP3486168A1

    公开(公告)日：2019-05-22

    申请号：EP18195578.2

    申请日：2018-09-19

    Applicant: Bell Helicopter Textron Inc.

    Inventor： EWING, Alan Carl ,  GONZALEZ, Eric Ricardo ,  ISAAC, Mark Loring ,  STAMPS, Frank Bradley

    IPC: B64C27/26 ,  B64C27/28 ,  B64C29/00 ,  B64C39/08 ,  G05D1/08 ,  B64C15/12 ,  B64C27/30 ,  B64C27/08 ,  B64C11/28

    Abstract: A quad tiltrotor aircraft (10, 100, 200) has a longitudinally extending fuselage (12, 312) with forward and aft stations (14, 314; 16, 318). A forward wing (18, 320) having first and second outboard ends extends laterally from the forward station (14, 314). An aft wing (20, 324) having first and second outboard ends extends laterally from the aft station (16, 318). First and second forward rotors (26a, 26b, 112a, 112b, 212a, 212b, 330a, 330b) are respectively coupled proximate the first and second outboard ends of the forward wing (18, 320) and are tiltable relative to the forward wing (18, 320) between vertical lift and forward thrust orientations. First and second aft rotors (36a, 36b, 120a, 120b, 220a, 220b, 342a, 342b) are respectively coupled proximate the first and second outboard ends of the aft wing (20, 324) and are tiltable relative to the aft wing (20, 324) between vertical lift and forward thrust orientations. The forward rotors (26a, 26b, 112a, 112b, 212a, 212b, 330a, 330b) are higher disk-loading rotors than the aft rotors (36a, 36b, 120a, 120b, 220a, 220b, 342a, 342b). The aft rotors (36a, 36b, 120a, 120b, 220a, 220b, 342a, 342b) are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft (10, 100, 200).

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