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公开(公告)号：US20200031086A1
公开(公告)日：2020-01-30
申请号：US16048869
申请日：2018-07-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Mark Mays , Michael Christopher Burnett
IPC: B32B1/08 , B64C27/473 , B64C3/18 , B32B27/08
Abstract: Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.
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公开(公告)号：US10543913B2
公开(公告)日：2020-01-28
申请号：US15882287
申请日：2018-01-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Tyler Wayne Baldwin , Kyle Thomas Cravener , Andrew Maresh
Abstract: A tri-hybrid yoke including a center ring connected to a CF fitting connected to flexure arms. An inboard centrifugal force bearing assembly connects to the CF fitting and a grip. An outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center ring and the CF fittings carry the centrifugal force at a position inboard of the flexure arm.
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公开(公告)号：US20200025661A1
公开(公告)日：2020-01-23
申请号：US16124762
申请日：2018-09-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Xiaoming Li , Bogdan R. Krasnowski , Robert A. Figueroa , Robert Wardlaw
Abstract: A notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer; isolating the notch; and selectively etching the notch to provide an etched surface of the notch; wherein at least a portion of the re-melt material layer has been removed from the notch. In one aspect, there is provided a notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer, the specimen includes steel or an alloy thereof; isolating the notch; and selectively etching the notch with a first etching solution and a second etching solution to provide an etched surface on the notch; wherein at least a portion of the re-melt material layer has been removed from the notch.
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公开(公告)号：US20200017213A1
公开(公告)日：2020-01-16
申请号：US16031786
申请日：2018-07-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Levi Charles Hefner , Dakota Charles Easley
Abstract: An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each selectively rotatably coupled to the leading edge by a locking joint. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration, each motor mount is locked substantially perpendicular with the leading edge by the respective locking joint. In a compact storage configuration, each motor mount is locked substantially parallel with the leading edge the respective locking joint.
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公开(公告)号：US20200017190A1
公开(公告)日：2020-01-16
申请号：US16033695
申请日：2018-07-12
Applicant: Bell Helicopter Textron Inc.
Inventor： George R. Decker , Tjepke Heeringa
Abstract: A wing is provided in one example embodiment and may include an upper skin portion; a lower skin portion; and a multi-spar element that extends between the upper skin portion and the lower skin portion, wherein the multi-spar element comprises a plurality of spar elements integrated together. The multi-spar element may include at least one spar element that extends between the upper skin portion and the lower skin portion, wherein the at least one spar element is continuously connected along a forward and aft directional axis to at least one other spar element that extends between the upper skin portion and the lower skin portion. The multi-spar element may be attached to the upper skin portion and the lower skin portion.
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Patent Agency Ranking
公开(公告)号：US20200001986A1
公开(公告)日：2020-01-02
申请号：US16019826
申请日：2018-06-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Mark Wiinikka , Scott Hemmen , Nathan P. Green , James Blake
Abstract: A strut assembly for a vibration isolation device is disclosed, comprising a piston spindle; a first elastomeric member and a second elastomeric member bonded to the piston spindle and in contact with an upper housing and a lower housing, respectively; a first strut support and a second strut support attached to or integral with the upper housing and the lower housing, respectively; a first strut spindle and the second strut support configured to be placed in the first strut support and the second strut support, respectively; and one or more removable struts configured to be engaged to the first strut spindle and to the second strut spindle, wherein at least one of the first or second strut spindles is removable such that the one or more struts can be replaced without breaking a bonding of the first elastomeric member, the second elastomeric member, or both.
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107.发明申请公开(公告)号：US20200001979A1
公开(公告)日：2020-01-02
申请号：US16401332
申请日：2019-05-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Kyle Thomas CRAVENER , Brady Garrett ATKINS , Stuart Benjamin COOK , Joaquin VARGAS CALVET , Andrew Michael WHITE , Karl BAILEY , Corrine JAGNEAUX , Maika Lopati MAUGA
Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.
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公开(公告)号：US20190389569A1
公开(公告)日：2019-12-26
申请号：US16016280
申请日：2018-06-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Ken Shundo
Abstract: A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.
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公开(公告)号：US10513982B2
公开(公告)日：2019-12-24
申请号：US15439728
申请日：2017-02-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Zachary Edwin Dailey , Frank Bradley Stamps , Martin Peryea
IPC: B64D33/08 , F02C7/36 , F02C7/141 , F02C7/232 , F02C9/40 , F02C7/16 , F02C3/30 , F02C7/22 , F02C7/143 , F02C9/28 , B64C27/00 , B64D33/02
Abstract: A rotorcraft has a low density altitude flight mode and a high density altitude flight mode. The rotorcraft includes a turboshaft engine forming a gas path in sequence through an air inlet section, a compressor section, a combustor section, a turbine section and an exhaust section. A drive system is coupled to the engine and is operable responsive to rotation of at least a portion of the turbine section. A rotor is coupled to the drive system and is operable to receive torque and rotational energy therefrom. A fuel injection system supplies fuel to the combustor section. An oxidizer injection system and a coolant injection system are used to selectively inject an oxidizer and a coolant into the gas path when it is desired to operate the rotorcraft in the high density altitude flight mode, thereby increasing the altitude density ceiling of the rotorcraft for maneuvers including takeoffs and landings.
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公开(公告)号：US20190382140A1
公开(公告)日：2019-12-19
申请号：US16546025
申请日：2019-08-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Sébastien Giroux , Cédric Roche
Abstract: A system and method for performing a test procedure on a system under test are provided. An actuation unit operatively coupled to the system under test is configured to perform at least one operation thereon. A visual recognition unit is configured to capture at least one image of the system under test in real-time. A test unit remotely interfaced with the system under test is configured to perform the test procedure. Using the test unit, the test procedure is retrieved from the memory, at least one control signal is output to the actuation unit for causing the at least one operation to be performed in real-time for testing the system under test in accordance with the one or more test instructions, and the at least one image of the system under test is monitored as the at least one operation is performed for validating the test procedure in real-time.
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