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公开(公告)号：US10220951B2
公开(公告)日：2019-03-05
申请号：US15410706
申请日：2017-01-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Bruce Bennett Bacon , Michael Edwin Rinehart , Thomas Boudreau
IPC: B64D27/26 , B64C29/00 , F02C7/20 , F16F15/06 , B64C27/00 , B64D27/00 , B64D29/02 , F16B2/06 , B64D27/10 , F16F1/16
Abstract: A rotorcraft, such as a tiltrotor aircraft having helicopter and airplane modes, includes an airframe, an engine and an engine mount assembly for coupling the engine to the airframe. The engine includes an engine lug forming an aperture. The engine mount assembly includes a mount having an aperture substantially aligned with the engine lug aperture. A sleeved bolt assembly extends through the apertures to secure the engine lug to the mount. The sleeved bolt assembly includes a bolt undersized relative to the apertures forming a circumferential gap within the apertures, a sleeve disposed around at least a portion of the bolt substantially filling the circumferential gap and a nut adapted to thread onto a threaded portion of the bolt. The use of the undersized bolt within the sleeve permits increased clearance between the sleeved bolt assembly and the engine while maintaining strength requirements in high load environments.
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公开(公告)号：US10220942B2
公开(公告)日：2019-03-05
申请号：US15241529
申请日：2016-08-19
Applicant: Bell Helicopter Textron Inc.
Inventor： John Robert Wittmaak
Abstract: In some embodiments, a rotorcraft includes a fuselage having a rotor hub assembly protruding therefrom that is rotatable relative thereto. A generator having an armature is mechanically coupled to the rotor hub assembly such that the armature is rotatable in response to rotation of the rotor hub assembly. A braking unit is in selective electrical communication with the generator. The braking unit is adapted to apply an electrical resistance to rotation of the armature, thereby reducing a rotational speed of the rotor hub assembly.
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公开(公告)号：US20190061925A1
公开(公告)日：2019-02-28
申请号：US15688165
申请日：2017-08-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson , Brett Rodney Zimmerman
Abstract: A cargo transportation system includes a cargo platform having an upper surface and a perimeter. A propulsion system is disposed about the perimeter of the cargo platform. The propulsion system includes a plurality of propulsion assemblies, each including a propulsion unit disposed within a housing defining an airflow channel having an air inlet for incoming air and an air outlet for outgoing air such that the outgoing air is operable to generate at least vertical lift. A power system disposed within the cargo platform provides energy to drive the propulsion system. A flight control system operably associated with the propulsion system and the power system controls flight operations of the cargo transportation system.
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公开(公告)号：US20190061915A1
公开(公告)日：2019-02-28
申请号：US15693397
申请日：2017-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Gary Miller , Frank B. Stamps
CPC classification number: B64C11/32 , B64C11/06 , B64C11/30 , B64C27/605 , B64C29/0033 , B64C2027/7216 , B64C2027/7255
Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
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公开(公告)号：US20190056734A1
公开(公告)日：2019-02-21
申请号：US16032928
申请日：2018-07-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Earl Worsham, II , Luke Dafydd Gillett , Troy Sheldon Caudill , Bradley Paul Regnier , Joshua Robert O'Neil , Brandon Jeffrey Thomas
Abstract: In an embodiment, a rotorcraft includes a rotor system including a plurality of blades; two or more engines operable to rotate the plurality of blades; a control assembly operable to receive commands from a pilot; a flight control computer (FCC) in signal communication with the two or more engines, the FCC being operable to generate engine data indicating whether the two or more engines are functional; and a flight management system (FMS) in signal communication with the control assembly and the FCC, the FMS being operable to receive a takeoff type and a plurality of takeoff parameters input into the FMS by the pilot; generate a guidance profile for a Category A (Cat-A) takeoff procedure based on the takeoff type and the plurality of takeoff parameters, the Cat-A takeoff procedure including one or more decision points for performing a takeoff procedure based on whether all engines are operable or one engine is inoperable; receive a command to engage in a takeoff procedure from the control assembly; in response to the command to engage in the takeoff procedure, provide guidance cues to a pilot of the rotorcraft; receive the engine data from the FCC during operation of the rotorcraft; and update the guidance profile based on the engine data during operation of the rotorcraft.
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Patent Agency Ranking
公开(公告)号：US20190055004A1
公开(公告)日：2019-02-21
申请号：US15679645
申请日：2017-08-17
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph M. Schaeffer , Luke Dafydd Gillett
Abstract: A method for operating a rotorcraft includes providing a power hold by performing monitoring one or more operational parameters of the rotorcraft during flight, determining whether operational parameters need adjustment according to a relationship between the operational parameters and operating limits associated with a power setting for the power hold, and determining a flight parameter for one or more flight control devices of the rotorcraft in response to determining that the operational parameters need adjustment. Providing the power hold further includes sending a position set signal to a trim assembly of the rotorcraft to set a first position of a pilot control connected to the trim assembly according to a pilot control setting generated according to the flight parameter, and controlling a flight control device control according to a second position of the pilot control.
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公开(公告)号：US10207793B2
公开(公告)日：2019-02-19
申请号：US15365061
申请日：2016-11-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric R. Gonzalez , Frank B. Stamps
IPC: B64C11/18 , B64C27/467 , B64C27/35 , B64C27/52 , B64C27/473 , B64C11/20 , B64C29/00
Abstract: A rotor blade including a root portion adapted to be connected to a helicopter rotor hub for rotation therewith, the root portion having a first edge surface; a first movable member having a first movable surface adjacent to the first edge surface; a first elastomeric joint disposed between the root portion and the first movable member, the first elastomeric joint having an inner surface facing the first edge surface of the root portion and an outer surface facing the movable surface of the first movable member; and an actuating system mounted within the root portion and the first movable member for moving the first movable member. The first elastomeric joint deforms to adjust for shear from actuation of the first movable member to a first position during helicopter mode; and to a second position during airplane mode.
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公开(公告)号：US20190047692A1
公开(公告)日：2019-02-14
申请号：US16051343
申请日：2018-07-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Troy Cyril Schank , Andrew Ryan Maresh , Chyau-Song Tzeng
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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公开(公告)号：US20190047691A1
公开(公告)日：2019-02-14
申请号：US16051334
申请日：2018-07-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Troy Cyril Schank , Andrew Ryan Maresh , Chyau-Song Tzeng
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 propulsion assembly includes a gimbal lock assembly positioned about the mast and including a plurality of radially outwardly extending and circumferentially distributed rollers. The gimbal lock assembly is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. In the disengaged position, the gimbal lock assembly enables the gimballing degree of freedom. In the engaged position, the rollers of the gimbal lock assembly contact the proprotor hub assembly to disable the gimballing degree.
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公开(公告)号：US20190039713A1
公开(公告)日：2019-02-07
申请号：US15665627
申请日：2017-08-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Jon Damon Bennett , Joshua Allan Edler
Abstract: One example of a fairing for a rotorcraft includes an outer mold line portion (OML portion) and a bearing portion extending from the OML portion. The OML portion provides at least a portion of an outer mold line of the rotorcraft. Both the OML portion and the bearing portion shield a portion of a structural member. The bearing portion can protect the portion of the structural member from damage resulting from foot traffic associated with accessing an area nearby the structural member.
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