Patents Assigned to Bell Textron Inc.
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Publication number: 20220255160Abstract: A cold plate is couplable with a component for dissipating heat from a component. The cold plate includes a top plate coupled with a bottom plate to receive a cooling medium therebetween. The top plate includes a body and a plurality of walls extending from the body, wherein each wall of the plurality of walls includes a recess extending within the wall. The bottom plate includes a body and a plurality of walls extending from the body such that an end portion of each wall of the bottom plate is inserted within the recess of each wall of the top plate to form an interlocking joint.Type: ApplicationFiled: February 10, 2021Publication date: August 11, 2022Applicant: Bell Textron Inc.Inventors: William A. Amante, Jeffrey B. Cloud
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Publication number: 20220255175Abstract: A battery assembly for an aircraft includes a cold plate having an upper planar member, a lower planar member, and at least one fluid channel positioned between the upper and lower planar members and configured to receive a cooling fluid. The battery assembly also includes an upper battery mounted to the upper planar member for transferring heat from the upper battery to the cooling fluid through the upper planar member. The battery assembly further includes a lower battery mounted to the lower planar member for transferring heat from the lower battery to the cooling fluid through the lower planar member.Type: ApplicationFiled: February 10, 2021Publication date: August 11, 2022Applicant: Bell Textron Inc.Inventors: William A. Amante, Steven Loveland, Jessica A. Revere
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Publication number: 20220255159Abstract: An aircraft includes a fuselage and an airframe supporting the fuselage. The airframe includes a pair of longitudinally-extending beams. The aircraft further includes a battery assembly including a cold plate secured to the pair of longitudinally-extending beams, and a battery mounted to the cold plate.Type: ApplicationFiled: February 10, 2021Publication date: August 11, 2022Applicant: Bell Textron Inc.Inventors: William A. Amante, Karl H. Schroeder, Jessica A. Revere
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Publication number: 20220243726Abstract: A pump assembly, comprising a pump and housing having an inlet passage and an outlet passage. The pump includes inlet and outlet ports and opposing first and second drive inputs configured to be rotated together in a pumping direction to operate the pump. The pump can be installed in the housing in a first orientation, in which the first drive input is configured for being rotated by a drive source in a first external direction to operate the pump, and a second orientation, in which the second drive input is configured for being rotated by the drive source in a second external direction opposite of the first external direction to operate the pump. In both the first orientation and the second orientation, the inlet port is in fluid communication with the inlet passage and the outlet port is in fluid communication with the outlet passage.Type: ApplicationFiled: February 4, 2021Publication date: August 4, 2022Applicant: Bell Textron Inc.Inventors: Ezra Mike Tiprigan, Charles Hubert Speller
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Publication number: 20220243666Abstract: A fuel sample extractor (FSE) for an aircraft includes a sample chamber, a lid configured to seal the sample chamber, a pump in selective fluid communication with an upper portion of the sample chamber, and a straw in selective fluid communication with a lower portion of the sample chamber and a fuel tank.Type: ApplicationFiled: February 4, 2021Publication date: August 4, 2022Applicant: Bell Textron Inc.Inventor: Ralph Michael Gannarelli
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Publication number: 20220242584Abstract: An aircraft includes fuselage, a seat, and battery compartment. Fuselage extends along a longitudinal axis. Seat is configured to support a passenger. The battery compartment that includes a battery configured to provide power to propel the aircraft. The battery compartment, including the battery, is located laterally adjacent to the seat along the longitudinal axis.Type: ApplicationFiled: January 29, 2021Publication date: August 4, 2022Applicant: Bell Textron Inc.Inventors: Steven R. Ivans, Kirk L. Groninga
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Publication number: 20220234713Abstract: The current disclosure describes a cloaking system for an aircraft. Cameras on the aircraft can detect background colors during flight. Electroluminescent paint on the aircraft can be powered on that resembles the background color. The color and luminescence of the aircraft will allow for dynamic cloaking unachievable by prior art camouflage paint colors.Type: ApplicationFiled: January 28, 2021Publication date: July 28, 2022Applicant: Bell Textron Inc.Inventor: Adam S. Menard
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Publication number: 20220234728Abstract: A vertical takeoff and landing aircraft is described in which rotors can be disposed underneath the booms. This will allow for zero downward force resulting from thrust on the aircraft and therefore greater energy efficiency. Retractable doors can shield the rotors when not in use, decreasing drag during forward flight.Type: ApplicationFiled: January 22, 2021Publication date: July 28, 2022Applicant: Bell Textron Inc.Inventors: Kirk L. Groninga, Danielle L. Moore
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Publication number: 20220234310Abstract: A method of preparing a composite article including providing a first bias assembly with a first bias roll; providing a first non-bias assembly with a first non-bias roll; positioning the first bias assembly to a dispensing position; dispensing a bias ply from the first bias roll along a bias path on a mold; cutting the bias ply; positioning the first non-bias assembly to a dispensing position; dispensing a non-bias ply from the first non-bias roll; and cutting the non-bias ply; wherein the bias path and the non-bias path are substantially parallel.Type: ApplicationFiled: October 22, 2021Publication date: July 28, 2022Applicant: Bell Textron Inc.Inventors: David G. Carlson, Paul K. Oldroyd, George R. Decker, Doug K. Wolfe
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Publication number: 20220233898Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction. The nozzle has at least one opening and is configured to allow liquid to drain out of the at least one opening instead of allowing the liquid to flow into the at least one agent tube. The nozzle may have a chamfer opening that faces downward.Type: ApplicationFiled: January 26, 2021Publication date: July 28, 2022Applicant: Bell Textron Inc.Inventors: Thomas Dewey Parsons, Keith David Weaver, Chris James Ludtke, Paul Madej, Andrew Jordan Birkenheuer
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Publication number: 20220230551Abstract: Methods and systems are described for increasing the safety of unmanned vehicles. Failure rates of components can be combined and adjusted if necessary given sensor data or statistical or historical data that impacts failure rates. The failure rates of components can be combined to give an overall failure or success rate for a vehicle and can be compared to an accepted failure or success rate in connection with a hazard. Hazards with heightened safety requirements can be avoided by a contingency maneuver if the unmanned vehicle's failure or success rate is not acceptable.Type: ApplicationFiled: January 21, 2021Publication date: July 21, 2022Applicant: Bell Textron Inc.Inventors: John R. Wittmaak, JR., Joshua A. Edler, Alan H. Steinert, Joshua A. Duckett
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Publication number: 20220219810Abstract: In an embodiment, an aircraft includes a pilot input device, a position sensor coupled to the pilot input device, a flight condition sensor and a flight control computer (FCC). The FCC includes a first microprocessor and a second microprocessor. The first microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a first output. The second microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a second output. The FCC is configured to compare the first output and the second output to yield resultant data. Responsive to a determination that the first output and the second output do not match, the FCC is configured to execute first remediation logic if the resultant data satisfies first error criteria and to execute second remediation logic if the resultant data satisfies second error criteria.Type: ApplicationFiled: January 11, 2021Publication date: July 14, 2022Applicant: Bell Textron Inc.Inventors: Clifton L. HARRELL, Charles Eric COVINGTON, David A. ADJEI, Kevin Matthew TRENDEL, Michael David TRANTHAM, Randall JOHNSON
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Publication number: 20220219821Abstract: An inflatable pod assembly for an aircraft includes an expandable exoskeleton. The expandable exoskeleton defines a leading edge and a trailing edge of the inflatable pod assembly, and the expandable exoskeleton includes first and second portions selectively attachable to each other. The inflatable pod assembly also includes an internal cargo area configured to receive cargo, and the first and second portions are configured to selectively enclose the internal cargo area when the first and second portions are attached to each other. The inflatable pod assembly further includes an internal inflation chamber configured to selectively receive an inflation fluid for expanding the exoskeleton to thereby transition the inflatable pod assembly from a deflated state to an inflated state.Type: ApplicationFiled: January 11, 2021Publication date: July 14, 2022Applicant: Bell Textron Inc.Inventor: Justin A. Rivera
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Publication number: 20220212550Abstract: Embodiments are directed to a fuel cell protection system comprising an aircraft fuselage having an inner surface and an outer surface, an attachment point mounted on the outer surface, an aircraft fuel cell spaced apart from the inner surface, and a plate positioned between the inner surface and the aircraft fuel system, the plate spaced apart from the inner surface to create a void space. The attachment point may be a cargo hook. The void space is configured to receive all or a portion of the cargo hook after a crash. The plate creating the void space may be a rigid material or may be a ballistic fabric material.Type: ApplicationFiled: January 7, 2021Publication date: July 7, 2022Applicant: Bell Textron Inc.Inventors: Timothy Brian Carr, Douglas Howard Hamelwright, Joshua Andrew Emrich
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Publication number: 20220204154Abstract: A wing for an aircraft includes a first end, a second end, and a skin extending longitudinally from the first end to the second end. The wing also includes at least one channel positioned within the skin and extending longitudinally between the first and second ends. The at least one channel defines a longitudinal translation path for translating at least one electrical power source longitudinally between the first and second ends.Type: ApplicationFiled: December 31, 2020Publication date: June 30, 2022Applicant: Bell Textron Inc.Inventors: Robert W. Roe, Mark L. Isaac
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Publication number: 20220195946Abstract: Embodiments are directed to systems and methods for controlling an aircraft engine inlet comprises determining a required engine RPM for an engine in-flight restart based upon current aircraft parameters, detecting a command to initiate the engine in-flight restart, and managing a position of an engine inlet barrier to control a volume of air entering an engine intake, wherein the ram air causes an engine turbine to achieve the required engine RPM. The required engine RPM may be an N1 gas generator RPM. The engine inlet barrier may be a hinged door positioned within the engine inlet or a series of inlet variable guide vanes that are configured to rotate between a closed position and an opened position. The position of the engine inlet barrier may be controlled by a flight control computer or an engine control computer.Type: ApplicationFiled: December 22, 2020Publication date: June 23, 2022Applicant: Bell Textron Inc.Inventor: Thomas Dewey Parsons
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Publication number: 20220200703Abstract: Embodiments are directed to systems and methods for providing light communication (LC) for an aircraft. An LC transmitter is mounted on an aircraft fuselage and is configured to broadcast light signals within a defined region outside the aircraft. An LC receiver mounted on the aircraft fuselage is configured to receive light signals broadcast by a remote LC device. A controller is configured to manage LC signals in the aircraft, and an interface is provided between the controller and an aircraft data network. The light signals may be in a visible light spectrum, an invisible light spectrum, or both. The remote LC device may be, for example, a ground station, an aircraft, a ground vehicle, a ship, a building, or a portable transmitter.Type: ApplicationFiled: December 21, 2020Publication date: June 23, 2022Applicant: Bell Textron Inc.Inventors: Daniel Duane Donley, Michael Raymond Hull
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Publication number: 20220185469Abstract: A pylon conversion actuator, for use in tiltrotor aircraft, that converts the tiltrotor between hover flight mode and forward flight mode. Pylon conversion actuator selectively retracts and extends between a retracted position to an extended position. Pylon conversion actuator includes an extendable arm, a motor, and an actuator platform.Type: ApplicationFiled: December 11, 2020Publication date: June 16, 2022Applicant: Bell Textron Inc.Inventors: William ATKINS, George Ryan DECKER, Steven Allen ROBEDEAU, JR.
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Publication number: 20220187223Abstract: A method of evaluating fatigue damage of a rotor mast. The method includes performing an x-ray diffraction (“XRD”) inspection of the rotor mast, assessing fatigue damage sustained by the rotor mast based on results of the XRD inspection, and determining whether the rotor mast is suitable for continued use based on the assessed fatigue damage.Type: ApplicationFiled: December 10, 2020Publication date: June 16, 2022Applicant: Bell Textron Inc.Inventors: Steve CATES, Caydn WHITE, Kevin BROOKER
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Patent number: 11358729Abstract: An exemplary tiltrotor aircraft with a hybrid drive system includes a first propulsion system having a first engine and a first supplemental driver operably coupled to a first proprotor that is operable between a helicopter mode and an airplane mode and a second propulsion system having a second engine and a second supplemental driver operably coupled to a second proprotor that is operable between a helicopter mode and an airplane mode.Type: GrantFiled: January 28, 2021Date of Patent: June 14, 2022Assignee: Bell Textron Inc.Inventors: Colton James Gilliland, Mark Alan Przybyla, Eric Stephen Olson