Patents by Inventor Andrew Paul Haldeman
Andrew Paul Haldeman has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20200290735Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.Type: ApplicationFiled: March 15, 2019Publication date: September 17, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Aaron Alexander Acee, Andrew Paul Haldeman, Eric Albert Sinusas, Yann Lavallee, Albert G. Brand
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Publication number: 20200290732Abstract: A tension-torsion strap, for example for a rotor aircraft, including a continuous length of carbon fiber tow arranged in multiple loops to form an elongated member extending between opposing ends and a flexible cover encasing the carbon fiber tow.Type: ApplicationFiled: March 15, 2019Publication date: September 17, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Andrew Paul HALDEMAN, Gary MILLER
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Patent number: 10773798Abstract: An aircraft rotor assembly has a yoke and a plurality of rotor blade assemblies coupled thereto. Each of the rotor blade assemblies include a rotor blade, a bearing, and a blade grip coupling the rotor blade to the bearing. Each of the rotor blades is rotatable about a lead-lag axis, flap axis, and a pitch change axis, wherein all the axes intersect within the bearing. Adjacent pairs of rotor blade assemblies are coupled together via a damper assembly that is coupled to the pitch change axis of each of the rotor blade assemblies.Type: GrantFiled: September 29, 2017Date of Patent: September 15, 2020Assignee: Bell Textron Inc.Inventors: Andrew Paul Haldeman, Dalton T. Hampton, Bryan Marshall, Frank Bradley Stamps
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Patent number: 10752349Abstract: 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.Type: GrantFiled: October 29, 2018Date of Patent: August 25, 2020Assignee: Bell Helicopter Textron Inc.Inventors: Andrew Paul Haldeman, Zachary Edwin Dailey, Aaron Alexander Acee, Dalton T. Hampton
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Patent number: 10752346Abstract: 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.Type: GrantFiled: October 18, 2017Date of Patent: August 25, 2020Assignee: Textron Innovations Inc.Inventors: Andrew Paul Haldeman, Dalton T. Hampton, Frank Bradley Stamps, John Lloyd, Gilberto Morales
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Publication number: 20200262552Abstract: A method of controlling a tail rotor system of a helicopter includes pivoting a swashplate of the tail rotor system about an axis passing through a diameter of the swashplate. Pivoting the swashplate causes a first linkage of a first pair of linkages coupled between the swashplate and a collective crosshead to move in a first direction and a second linkage of the first pair of linkages coupled between the swashplate and the collective crosshead to move in a second direction that is opposite the first direction. The movement of the first and second linkages causes a plane of rotation of a pair of rotors of the tail rotor system to cant relative to a centerline of a mast of the tail rotor system.Type: ApplicationFiled: February 15, 2019Publication date: August 20, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Aaron Alexander ACEE, Andrew Paul Haldeman, Colin John Thomas
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Publication number: 20200247535Abstract: 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.Type: ApplicationFiled: February 3, 2019Publication date: August 6, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Aaron Alexander Acee, Andrew Paul Haldeman
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Publication number: 20200198781Abstract: A duct configured with a fan to increase thrust. The duct includes an interior surface configured to surround a rotation axis of the fan. The interior surface includes a nozzle portion configured to be located upstream of the fan and a diffuser portion configured to be located downstream of the fan. The interior surface defines an opening configured to introduce additional airflow along the diffuser portion.Type: ApplicationFiled: December 23, 2018Publication date: June 25, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Andrew Paul Haldeman, Frank Bradley Stamps, John Lloyd, Aaron Alexander Acee, Dalton T. Hampton, Albert Gerard Brand
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Publication number: 20200140077Abstract: A bidirectional aircraft rotor for a rotorcraft tail rotor. The rotorcraft tail rotor uses a hub and a first tail rotor blade affixed to the hub. A pitch of the first tail rotor blade is fixed, and a profile of a leading edge of the first tail rotor blade is identical to a profile of a trailing edge of the first tail rotor blade. The tail rotor is driven by a torque source, such as an electric motor or an engine. The tail rotor uses variable RPM and reversible rotational direction to provide rotorcraft with yaw control.Type: ApplicationFiled: November 1, 2018Publication date: May 7, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Aaron Alexander Acee, Andrew Paul Haldeman
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Publication number: 20200130823Abstract: 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.Type: ApplicationFiled: October 29, 2018Publication date: April 30, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Andrew Paul HALDEMAN, Zachary Edwin Dailey, Aaron Alexander Acee, Dalton T. Hampton
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Patent number: 10633084Abstract: In one embodiment, a method may comprise coupling a plurality of reinforcement fibers to a plurality of spherical components; inserting the plurality of spherical components into an enclosure; and heating the enclosure to cause the plurality of spherical components to expand, wherein the plurality of spherical components expands to form a geodesic structure, wherein the geodesic structure comprises a plurality of polyhedron components configured in a geodesic arrangement.Type: GrantFiled: August 25, 2017Date of Patent: April 28, 2020Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Dalton T. Hampton, Timothy Kent Ledbetter, Drew A. Sutton, Bryan W. Marshall, Paul Sherrill, Frank B. Stamps, James Donn Hethcock, Andrew Paul Haldeman, Paul K. Oldroyd
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Publication number: 20200094450Abstract: 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.Type: ApplicationFiled: September 25, 2018Publication date: March 26, 2020Inventors: James A. Cordell, Suvankar Mishra, Andrew Paul Haldeman, Jesse J. Wrabel, Dalton T. Hampton
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Patent number: 10597143Abstract: In one embodiment, a rotor hub comprises a hub body, and a plurality of blade grips configured for attaching a plurality of rotor blades. The rotor hub further comprises a plurality of centrifugal force bearings coupled to the plurality of blade grips, wherein a focus of the plurality of centrifugal force bearings is aligned with a centerline of a rotor mast. The rotor hub further comprises a plurality of drive links configured to transfer torque to the plurality of rotor blades, wherein the plurality of drive links is positioned to correspond with a leading edge side of the plurality of rotor blades. The rotor hub further comprises a plurality of pitch horns configured to adjust a pitch of the plurality of rotor blades.Type: GrantFiled: August 22, 2017Date of Patent: March 24, 2020Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Andrew Paul Haldeman, Frank B. Stamps, James Donn Hethcock
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Patent number: 10597150Abstract: A rotor system includes a yoke, a plurality of blade grip assemblies and a plurality of centrifugal force bearings coupling the blade grip assemblies with the yoke. A plurality of rotor blades are coupled to the blade grip assemblies such that each rotor blade has a coincident hinge and such that each rotor blade has three independent degrees of freedom including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. A blade-to-blade damping ring includes a plurality of damper anchors each coupled to one of the blade grip assemblies along the respective pitch change axis and a plurality of lead-lag dampers each coupled between adjacent damper anchors. During blade pitch operations, each blade grip assembly is operable to rotate relative to the respective damper anchor, such that the blade-to-blade damping ring is operable to provide pitch independent lead-lag damping.Type: GrantFiled: April 24, 2018Date of Patent: March 24, 2020Assignee: Textron Innovations Inc.Inventors: Andrew Paul Haldeman, Dalton T Hampton, Frank Bradley Stamps
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Patent number: 10587103Abstract: A standpipe assembly for a rotorcraft includes a slip ring positioned within the mast of the rotorcraft. The slip ring includes a stator rotationally connected to a rotor. A flexible coupling is connected to the stator and a standpipe tube is connected to the flexible coupling. The flexible coupling is capable of angular, axial, and torsional displacement.Type: GrantFiled: March 16, 2018Date of Patent: March 10, 2020Assignee: Bell Helicopter Textron Inc.Inventors: Chad Jarrett, Andrew Paul Haldeman, Zachary Dailey
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Publication number: 20200039641Abstract: An abrasion strip and method of manufacturing the same. The abrasion strip being composed of INCONEL® alloy 718SPF™ and being shaped by superplastic forming.Type: ApplicationFiled: August 2, 2018Publication date: February 6, 2020Applicant: Bell Helicopter Textron Inc.Inventors: Andrew Paul Haldeman, Dalton T. Hampton, Aaron Alexander Acee, James Adrain Cordell
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Patent number: 10549840Abstract: 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.Type: GrantFiled: August 8, 2017Date of Patent: February 4, 2020Assignee: Textron Innovations Inc.Inventor: Andrew Paul Haldeman
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Patent number: 10494090Abstract: In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.Type: GrantFiled: September 8, 2017Date of Patent: December 3, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Jason C. Owens, Frank B. Stamps, Andrew Paul Haldeman, Robert P. Wardlaw, John R. McCullough, Gary Miller, Andrew Ryan Maresh, Drew A. Sutton
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Patent number: D894814Type: GrantFiled: September 27, 2019Date of Patent: September 1, 2020Assignee: Bell Textron Inc.Inventors: James Everett Kooiman, Michael Edwin Rinehart, Lynn Francis Eschete, Jason Paul Winter, Derek Ray Eddins, Steven Allen Robedeau, Jr., Clegg Benjamin Brian Smith, Mark Loring Isaac, Andrew Thomas Carter, Aaron Alexander Acee, Glenn Alan Shimek, Jared Mark Paulson, Andrew Paul Haldeman, Brent Chadwick Ross, Steven Ray Ivans
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Patent number: D896730Type: GrantFiled: September 27, 2019Date of Patent: September 22, 2020Assignee: Bell Textron Inc.Inventors: James Everett Kooiman, Michael Edwin Rinehart, Lynn Francis Eschete, Jason Paul Winter, Derek Ray Eddins, Steven Allen Robedeau, Jr., Clegg Benjamin Brian Smith, Andrew Thomas Carter, Aaron Alexander Acee, Andrew Paul Haldeman