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公开(公告)号：US11220329B2
公开(公告)日：2022-01-11
申请号：US16266086
申请日：2019-02-03
Applicant: Bell Helicopter Textron Inc.
Inventor： Aaron Alexander Acee , Andrew Paul Haldeman
Abstract: Systems and methods include providing an aircraft with a ducted rotor assembly. The ducted rotor assembly includes a housing having a duct, a rotor drive mechanism coupled to a rotor system, and a plurality of stators that both structurally support the rotor drive mechanism within the duct of the housing and carry a fluid through internal fluid passages in the plurality of stators to provide cooling to the rotor drive mechanism. Some of the stators carry fluid to the rotor drive mechanism, where the fluid absorbs heat from the rotor drive mechanism, and some of the stators carry fluid away from the rotor drive mechanism. The rotor system generates an airflow over the stators carrying fluid away from the rotor drive mechanism to effect transfer between the fluid and the airflow.
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公开(公告)号：US10549840B2
公开(公告)日：2020-02-04
申请号：US15672087
申请日：2017-08-08
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Paul Haldeman
Abstract: An adjustable balance module for the balancing of rotatable blades. The adjustable blade balance module includes a frame that retains and covers an adjustment screw with a mass that translates along a threaded shaft of the adjustment screw. The adjustment screw is incrementally controlled by an adjustment dial that is accessible from an exterior surface of the blade.
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公开(公告)号：US20190308722A1
公开(公告)日：2019-10-10
申请号：US15949660
申请日：2018-04-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Dalton T. Hampton , Andrew Paul Haldeman , Aaron Alexander Acee , Matthew John Hill
Abstract: Systems and methods include providing an aircraft with a tail rotor system having a tail rotor housing that forms a cambered airfoil between an upper cambered surface and an lower cambered surface of the tail rotor housing. The cambered airfoil design of the tail rotor housing is capable of providing sufficient lifting force of an aircraft to offload the tail rotor during forward flight, thereby eliminating the need for a traditional vertical stabilizer or fin. The tail rotor blades of the tail rotor system are disposed within an aperture in the tail rotor housing, which minimizes or preferably eliminates exposure of the tail rotor blades to edgewise airflow typically encountered during forward flight, thereby allowing rigid rotor hubs, both in-plane and out-of-plane, to be used in the tail rotor system while also reducing noise output of the tail rotor system.
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公开(公告)号：US10317323B2
公开(公告)日：2019-06-11
申请号：US15782677
申请日：2017-10-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Paul Haldeman , Ramesh Thiagarajan , Suvankar Mishra
Abstract: Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.
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公开(公告)号：US20190113426A1
公开(公告)日：2019-04-18
申请号：US15782677
申请日：2017-10-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Paul Haldeman , Ramesh Thiagarajan , Suvankar Mishra
IPC: G01N3/08
Abstract: Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.
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Patent Agency Ranking
公开(公告)号：US20190047682A1
公开(公告)日：2019-02-14
申请号：US15672087
申请日：2017-08-08
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Paul Haldeman
Abstract: An adjustable balance module for the balancing of rotatable blades. The adjustable blade balance module includes a frame that retains and covers an adjustment screw with a mass that translates along a threaded shaft of the adjustment screw. The adjustment screw is incrementally controlled by an adjustment dial that is accessible from an exterior surface of the blade.
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公开(公告)号：US11027465B2
公开(公告)日：2021-06-08
申请号：US16141127
申请日：2018-09-25
Applicant: Bell Helicopter Textron Inc.
Inventor： James A. Cordell , Suvankar Mishra , Andrew Paul Haldeman , Jesse J. Wrabel , Dalton T. Hampton
Abstract: A method is provided in one example embodiment and may include positioning at least one nozzle within a hollow portion of a rotor blade at a distance associated with a span of the rotor blade and providing, via the at least one nozzle, a liquid foam mixture in the hollow portion, wherein the liquid foam expands and becomes a solid foam material that fills the hollow portion of the rotor blade. Another method is provided in another example embodiment and may include providing a plurality of openings for a rotor blade that are positioned proximate to a hollow portion of the rotor blade and providing a liquid foam mixture in the hollow portion of the rotor blade through at least one opening of the rotor blade, wherein the liquid foam mixture expands and becomes a solid foam material that fills the hollow portion of the rotor blade.
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公开(公告)号：US10940944B2
公开(公告)日：2021-03-09
申请号：US15967220
申请日：2018-04-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Paul Haldeman , Zachary Edwin Dailey , Charles Owen Black , Dalton T. Hampton , Aaron Alexander Acee
Abstract: A transmission tilt control device includes a transmission rotatably coupled to an airframe of a helicopter, a rotor mast coupled to the transmission, and an actuator coupled between the transmission and the airframe. The actuator being configured to rotate the transmission fore and aft about a tilt axis that is perpendicular to an axis of rotation of the rotor mast.
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公开(公告)号：US10752349B2
公开(公告)日：2020-08-25
申请号：US16173064
申请日：2018-10-29
Applicant: Bell Helicopter Textron Inc.
Abstract: An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.
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公开(公告)号：US10752346B2
公开(公告)日：2020-08-25
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.
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