-
公开(公告)号：US20190112041A1
公开(公告)日：2019-04-18
申请号：US15787093
申请日：2017-10-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Paul Haldeman , Dalton T. Hampton , Frank Bradley Stamps , John Lloyd , Gilberto Morales
Abstract: A rotor assembly has a composite driveshaft extending between a transmission and a yoke for providing torque from the transmission to the yoke to cause rotation of the yoke and a plurality of rotor blade assemblies attached thereto. The rotor hub also has a composite static mast coupled to the yoke and a frame. The static mast being configured to carry the lift and thrust forces from the yoke to the frame.
-
公开(公告)号：US10261517B2
公开(公告)日：2019-04-16
申请号：US15484994
申请日：2017-04-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Mike Bothwell , Sung Kyun Kim , Jillian Samantha Alfred , Robert Earl Worsham, II , Luke Dafydd Gillett , Morganne Cody Klein
Abstract: A rotorcraft including a flight control computer (FCC) providing a vertical speed hold for the rotorcraft, a collective control, and a collective trim motor connected to the collective control. The collective trim motor moves the collective control according to a collective set command generated by the FCC according to a target vertical speed and when the FCC determines the collective control is in-detent. A collective position sensor is connected to the collective control. The collective position sensor generates, and sends to the FCC, a collective position signal indicating the position of the collective control. A flight control device controls a flight parameter of the rotorcraft in response to a flight control device control signal received from the FCC. The FCC generates the flight control device control signal according to the collective position signal, and sends the flight control device control signal to a flight control device.
-
公开(公告)号：US20190106203A1
公开(公告)日：2019-04-11
申请号：US15728989
申请日：2017-10-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Jon Damon Bennett , Joshua Allan Edler , Matthew Wade Hendricks
Abstract: One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.
-
公开(公告)号：US20190092462A1
公开(公告)日：2019-03-28
申请号：US16203931
申请日：2018-11-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey
Abstract: A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode includes a fuselage having a wing rotatably mounted thereto. The wing has an orientation generally perpendicular to the fuselage, in the flight modes, and an orientation generally parallel to the fuselage, in the storage mode. First and second pylon assemblies are positioned proximate outboard ends of the wing. First and second mast assemblies are respectively rotatable relative to the first and second pylon assemblies and have generally vertical orientations, in the VTOL flight mode, and generally horizontal orientations, in the forward flight mode and the storage mode. First and second proprotor assemblies are respectively rotatable relative to the first and second mast assemblies. Each proprotor assembly includes a plurality of rotor blades and has a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode.
-
公开(公告)号：US20190092458A1
公开(公告)日：2019-03-28
申请号：US15718592
申请日：2017-09-28
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd , Brett Rodney Zimmerman
IPC: B64C27/00 , B64C27/473 , B64C27/06
Abstract: An inertia weight assembly positionable within a receiving portion of a rotor blade for use on a rotorcraft. The inertia weight assembly includes a weighted core and a casing having a closed outboard end and forming a cavity. The weighted core is disposed in the cavity such that the casing at least partially encloses the weighted core. The weighted core is formed from a first material and the casing is formed from a second material that is dissimilar to the first material. The casing provides an interface between the weighted core and the receiving portion of the rotor blade. The second material is more bondable to the receiving portion of the rotor blade than the first material.
-
Patent Agency Ranking
公开(公告)号：US10239609B2
公开(公告)日：2019-03-26
申请号：US15656929
申请日：2017-07-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Hunter Jay Davis , Mark Adam Wiinikka
IPC: B64C27/54 , B64C27/605 , F16C7/06
Abstract: A system and method for measuring, or otherwise determining pitch length adjustments to a pitch link coupled to a rotor blade in a rotorcraft includes vertical track adjustment indicators machined onto an exterior of the tube of the pitch link and a vertical reference indicator machined onto an exterior of the upper or the lower rod of the pitch link. A metric of a pitch length adjustment can be determined by tracking or counting how many track adjustment indicators pass the reference indicator while the tube of the pitch link is being turned in either direction for increasing or decreasing the pitch length. The track adjustment indicators can be relied upon to track one or a series of adjustments for tracking a rotor blade installed in a rotor assembly.
-
公开(公告)号：US20190084685A1
公开(公告)日：2019-03-21
申请号：US15706338
申请日：2017-09-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Brent Scannell , Thomas Mast
Abstract: In one embodiment of the present disclosure, there is provided an aircraft having a bi-folding cowl for providing full access to equipment without completely removing the cowl. The bi-folding cowl has an upper portion and a lower portion mechanically connected along the adjacent edges, where the upper and lower portions fold so that the inner surfaces face each other when opened. In another embodiment, the bi-folding cowl has at least three maintenance positions, including partially-opened, fully-opened, and fully-opened, lying flat on the surface of the aircraft.
-
公开(公告)号：US20190084669A1
公开(公告)日：2019-03-21
申请号：US16196247
申请日：2018-11-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Brent C. Ross , Steven R. Ivans
Abstract: An aircraft is described and includes a fuselage, a wing coupled to the fuselage, and a rotor system including a proprotor system and an engine. An interconnect driveshaft gear is configured to communicate mechanical energy between a gearbox and an interconnect driveshaft. An accessory gear is coplanar with and in mechanical communication with the driveshaft gear. A proprotor gear is coplanar with and in mechanical communication with the interconnect driveshaft gear and the accessory gear and communicates mechanical energy to the proprotor system. An engine gear coplanar and in mechanical communication with the interconnect driveshaft ear, the accessory gear, and the proprotor gear transmits mechanical energy to the proprotor system via the proprotor gear.
-
公开(公告)号：US20190084207A1
公开(公告)日：2019-03-21
申请号：US15710797
申请日：2017-09-20
Applicant: Bell Helicopter Textron Inc.
Inventor： David G. Carlson , Douglas K. Wolfe , James A. Cordell
Abstract: In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form an assembly fixture, wherein the assembly fixture comprises an anisotropic thermal expansion property, and wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the assembly fixture.
-
公开(公告)号：US10232950B2
公开(公告)日：2019-03-19
申请号：US15200273
申请日：2016-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd
Abstract: In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.
-
-
-
-
-
-
-
-
-
Search Results
3499
records
(took 0.05 seconds)
