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公开(公告)号：US10289770B2
公开(公告)日：2019-05-14
申请号：US15092969
申请日：2016-04-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Jonathan A. Knoll , Jeffrey P. Nissen , John R. McCullough
IPC: G06F17/50
Abstract: A method of performing structural analysis relating to a component having CAD-based geometry, refined CAD-based geometry and CAD-based FEA data associated therewith. The method includes scanning the component to obtain scan-based point cloud geometry of the component, aligning the scan-based point cloud geometry with the CAD-based geometry of the component, generating scan-based geometry of the component by refining the scan-based point cloud geometry, comparing the scan-based geometry with the refined CAD-based geometry of the component to quantify geometric differences therebetween, generating scan-based FEA geometry of the component by meshing the scan-based geometry, performing finite element analysis on the scan-based FEA geometry to obtain scan-based FEA data and comparing the scan-based FEA data with the CAD-based FEA data of the component to quantify the effect of geometric difference therebetween.
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公开(公告)号：US10287012B2
公开(公告)日：2019-05-14
申请号：US15241436
申请日：2016-08-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga , Carlos Alexander Fenny
Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. A main lifting surface is supported by the forward portion of the fuselage. A propulsion system is operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of rotatably mounted tail arms having control surfaces and landing members wherein, in a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces and, wherein, in a landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.
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公开(公告)号：US10287010B2
公开(公告)日：2019-05-14
申请号：US15341905
申请日：2016-11-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Frank Bradley Stamps , Eric Ricardo Gonzalez
Abstract: An aircraft has a fuselage, a first rotor assembly having a first rotor hub and first rotor blades pivotably coupled to the first rotor hub and a second rotor assembly having a second rotor hub and second rotor blades pivotably coupled to the second rotor hub. The first and second rotor blades have deployed configurations extending generally radially from the fuselage and stowed configurations extending generally parallel with the fuselage. A sequencing cam, positioned between the first and second rotor hubs, is coupled to the second rotor blades. The sequencing cam has a retracted orientation when the second rotor blades are in the stowed configuration and an extended orientation when the second rotor blades are in the deployed configuration in which the sequencing cam props support arms of the first rotor blades preventing transition of the first rotor blades from the deployed configuration to the stowed configuration.
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公开(公告)号：US20190135411A1
公开(公告)日：2019-05-09
申请号：US15807843
申请日：2017-11-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric R. Gonzalez , Frank B. Stamps
Abstract: A multirotor aircraft comprises at least three proprotors. Each proprotor has a plurality of rotor blades pivotably attached to a mast assembly. When a rotor blade pitch angle is changed for a proprotor, all rotor blades on the proprotor change to a same pitch angle. The proprotors are configured to spin freely when a power source is disengaged or fails. In various embodiments, one or more engines provides power to each proprotor, or at least one engine provides power to two or more proprotors. A rotor blade control system is configured to control a collective rotor blade pitch angle on each proprotor independently of the rotor blade pitch on the other proprotors. The rotor blade control system is configured to set a negative collective rotor blade pitch angle on an unpowered proprotor, such as in response to manual inputs by a pilot or in response to current engine conditions.
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公开(公告)号：US10279901B2
公开(公告)日：2019-05-07
申请号：US15272062
申请日：2016-09-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Steven Ray Ivans , Brent Chadwick Ross
IPC: B64C29/00 , B64C39/02 , B64D27/02 , B64D33/02 , B64D33/04 , B64D35/04 , B64D35/08 , F16H35/00 , B64C3/18 , F16H1/20
Abstract: A propulsion system includes an engine disposed within a fuselage, a first gearbox coupled to the engine, a wing member having an upper wing skin and torque box formed by a first rib, a second rib, a first spar and second spar, a drive shaft coupled to the first gearbox and disposed within the wing member, a second gear box coupled to the drive shaft and disposed outboard from the second rib or inboard from the first rib, and a rotatable proprotor coupled to the second gear box. The rotatable proprotor includes a plurality of rotor blades, a rotor mast having a mast axis of rotation, and a proprotor gearbox coupled to the rotor mast. The proprotor gearbox is rotatable about a conversion axis, which intersects with the mast axis of rotation at a point within a central region of the torque box and above the upper wing skin.
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Patent Agency Ranking
公开(公告)号：US10279900B2
公开(公告)日：2019-05-07
申请号：US15233897
申请日：2016-08-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Bryan Robertson , Dudley Smith , Mark Dreier , Steve Ray Ivans , Kirk Landon Groninga
Abstract: In some embodiments, a rotorcraft includes a fuselage, a tailboom, a drive system and a variable thrust cross-flow fan system. The cross-flow fan system includes a cross-flow fan assembly that is mechanically coupled to a drive shaft and operable to rotate with the drive shaft about a longitudinal axis. The cross-flow fan assembly includes first and second driver plates having a plurality of blades rotatably mounted therebetween. The blades are disposed radially outwardly from the longitudinal axis and have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis. The blades are moveable between a plurality of pitch angle configurations. A control assembly is coupled to the blades. The control assembly is operable to change the pitch angle configuration of the blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly.
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公开(公告)号：US10279892B2
公开(公告)日：2019-05-07
申请号：US15252560
申请日：2016-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Bosworth
Abstract: A tiltrotor aircraft includes a fuselage supporting first and second wings each having an outboard end. First and second nacelles are respectively coupled to the outboard ends of the first and second wings. The first and second nacelles each have an outboard end. First and second wing extensions are rotatably coupled, respectively, to the outboard ends of the first and second nacelles. First and second actuators are operable to respectively move the first and second wing extensions to dampen a mode of the first and second wings, thereby stabilizing the tiltrotor aircraft.
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公开(公告)号：US20190130781A1
公开(公告)日：2019-05-02
申请号：US15928644
申请日：2018-03-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Paul Nissen , Daniel Brent McCall , Joshua Peter Riccobono
Abstract: Systems and methods include providing a virtual reality (“VR”) flight emulator system that simulates control, operation, and response of a vehicle. The flight emulator includes a control interface and a head-mounted display worn by a user. Motion, orientation, and/or forces experienced by the simulated vehicle are imparted to a user through a motion-control seat. Multiple flight emulators can be connected to a communication network, and a master flight emulator may teleport into a slave flight emulator in order to observe, overtake, override, and/or assume control of the slave flight emulator. Inputs made via the control interface of the master flight emulator or during playback of a pre-recorded training exercise or flight mission are translated into the control interface, head-mounted display, and motion-control seat of the slave flight emulator to provide real-time feedback to the user of the slave flight emulator.
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公开(公告)号：US10275950B2
公开(公告)日：2019-04-30
申请号：US13951900
申请日：2013-07-26
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： William D. Girard , Brian E. Tucker
IPC: G07C5/00
Abstract: A system and method configured to monitor aircraft flight performance data. The system includes a wireless transmitter in data communication with an avionics system of the aircraft, a portable wireless transceiver associated with the wireless transmitter, and a wireless database associated with the wireless transmitter. The method includes sensing flight performance data with the sensor, transmitting sensed flight performance data to the wireless transmitter, wirelessly transmitting the sensed flight performance data to the wireless database, and monitoring flight performance data with a display operably associated with the wireless database.
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公开(公告)号：US20190118942A1
公开(公告)日：2019-04-25
申请号：US15792430
申请日：2017-10-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung Kim , Jouyoung Jason Choi , Frank Bradley Stamps
Abstract: Systems and methods of operating a tiltrotor aircraft include providing a control system that includes sensors and/or gauges that provide feedback regarding hub shear forces in rotor systems of the aircraft that produce aeroelastic instability known as whirl flutter. Feedback from the sensors and/or gauges is communicated to a flight control subsystem that includes an algorithm that provides a cascading set of responses to control whirl flutter and a failsafe that adjusts operational characteristics of the aircraft in response to the continuation or excitation of the whirl flutter.
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