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公开(公告)号：US20220243666A1
公开(公告)日：2022-08-04
申请号：US17168064
申请日：2021-02-04
Applicant: Bell Textron Inc.
Inventor： Ralph Michael Gannarelli
Abstract: 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.
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公开(公告)号：US20220242557A1
公开(公告)日：2022-08-04
申请号：US17163785
申请日：2021-02-01
Applicant: Bell Textron Inc.
Inventor： Jonathan Andrew Knoll , George Matthew Thompson , Charles Hubert Speller , Grant Michael Beall
Abstract: A rotor system for an aircraft includes an open rotor assembly comprising an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.
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公开(公告)号：US20220230551A1
公开(公告)日：2022-07-21
申请号：US17154602
申请日：2021-01-21
Applicant: Bell Textron Inc.
Inventor： John R. Wittmaak, JR. , Joshua A. Edler , Alan H. Steinert , Joshua A. Duckett
Abstract: 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.
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公开(公告)号：US20220219817A1
公开(公告)日：2022-07-14
申请号：US17148307
申请日：2021-01-13
Applicant: Bell Textron Inc.
Inventor： Jonathan Andrew Knoll , George Matthew Thompson , Charles Hubert Speller , Grant Michael Beall
Abstract: A rotor system for an aircraft includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast via a yoke, wherein the rotor assembly is tiltable between a first position corresponding to an airplane mode and a second position corresponding to a helicopter mode; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast, the drive system comprising at least one electric motor for providing rotational energy to a drive shaft and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the drive shaft and providing rotational energy to the rotor mast via a rotor shaft; wherein the drive system is rotatable relative to the wing about a tilt axis and the rotor shaft is coaxial with the drive shaft.
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公开(公告)号：US20220219810A1
公开(公告)日：2022-07-14
申请号：US17145920
申请日：2021-01-11
Applicant: Bell Textron Inc.
Inventor： Clifton L. HARRELL , Charles Eric COVINGTON , David A. ADJEI , Kevin Matthew TRENDEL , Michael David TRANTHAM , Randall JOHNSON
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20220212550A1
公开(公告)日：2022-07-07
申请号：US17143387
申请日：2021-01-07
Applicant: Bell Textron Inc.
Inventor： Timothy Brian Carr , Douglas Howard Hamelwright , Joshua Andrew Emrich
Abstract: 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.
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公开(公告)号：US11378048B2
公开(公告)日：2022-07-05
申请号：US16864274
申请日：2020-05-01
Applicant: Textron Inc.
Inventor： Zekarias W. Yohannes , Matthew Wilcox , David Smith , Brian Moebs , Matthew D. Wilson , Russell William King
Abstract: A prime mover for a lightweight vehicle comprising an internal combustion engine, a starter motor integrally integrated with the internal combustion engine, and a housing for the prime mover. The prime mover additionally comprises a Hall Effect sensor and an prime mover control module structured and operable to communicate with the Hall Effect sensor, determine when operation of the internal combustion engine should cease, and upon the determination that operation of the internal combustion engine should cease, utilize the communication from the Hall Effect sensor to stop the internal combustion engine such that a piston of the internal combustion engine is positioned at between 15° and 25° after bottom-dead-center.
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公开(公告)号：US11377200B2
公开(公告)日：2022-07-05
申请号：US16733798
申请日：2020-01-03
Applicant: Bell Textron Inc.
Inventor： James Gibson , Carey Cannon
IPC: B64C13/04
Abstract: A control device for an aircraft has a control stick configured to be operated by hand of a user. The control stick is pivotable about a longitudinal axis, a lateral axis, and a yawing axis extending through the control stick. Motion of the stick about the longitudinal axis is configured to cause roll motion of the aircraft, motion of the stick about the lateral axis is configured to cause pitch motion of the aircraft, and motion of the stick about the yawing axis is configured to cause yaw motion of the aircraft. Rotation of a thumbwheel carried by the control stick changes a magnitude of a thrust vector of the aircraft.
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公开(公告)号：US11370544B2
公开(公告)日：2022-06-28
申请号：US16891947
申请日：2020-06-03
Applicant: Bell Textron Inc.
Inventor： Carlos A. Fenny , Brandon Anthony Magalhaes , Gary John Coleman, Jr.
Abstract: A system is described and includes a first track assembly for connecting a top surface of a pallet supporting payload to an upper interior surface of a payload bay of an aircraft; a second track assembly for connecting a side surface of the pallet to a side interior surface of the payload bay; and a pallet actuator system for selectively moving the pallet along the first and second track assemblies between a first position in which the pallet is fully extended from the payload bay and a second position in which the pallet is fully retracted into the payload bay.
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公开(公告)号：US20220195946A1
公开(公告)日：2022-06-23
申请号：US17130358
申请日：2020-12-22
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons
IPC: F02C9/20
Abstract: 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.
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