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公开(公告)号：US20240246664A1
公开(公告)日：2024-07-25
申请号：US18438266
申请日：2024-02-09
Applicant: Textron Innovations Inc.
Inventor： Frank Bradley Stamps , Michael Reaugh Smith , Bradley Joseph Passe
IPC: B64C27/00 , B64C27/10 , B64C27/22 , B64C27/26 , F16F15/167
CPC classification number: B64C27/001 , B64C27/10 , B64C27/22 , B64C27/26 , F16F15/167 , B64C2027/002 , F16F2222/08 , F16F2228/066 , F16F2230/18
Abstract: A compound helicopter includes a fuselage including a fuselage airframe, a translational thrust system coupled to the fuselage airframe and a pylon assembly subject to vibration. The pylon assembly includes a transmission and a rotor system having a main rotor assembly. The compound helicopter also includes a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency. Each augmented liquid inertia vibration eliminator unit includes at least one active tuning element movable to tune the isolation frequency thereof.
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公开(公告)号：US11203418B2
公开(公告)日：2021-12-21
申请号：US16717095
申请日：2019-12-17
Applicant: Textron Innovations Inc.
Inventor： Frank Bradley Stamps , Michael Reaugh Smith , Michael Scott Seifert
Abstract: A mount system for tiltably supporting a pylon assembly of a rotorcraft. First, second, third and fourth pylon links are each coupled between the pylon assembly and the airframe of the rotorcraft. The first pylon link has a first axis, the second pylon link has a second axis, the third pylon link has a third axis and the fourth pylon link has a fourth axis. Each of the axes intersects at a focal point located proximate a coaxial rotor system having counter-rotating upper and lower rotor assemblies such that the focal point provides a virtual pivot point about which the pylon assembly tilts to generate a control moment about a center of gravity of the rotorcraft that counteracts lateral and fore/aft moments generated by the upper and lower rotor assemblies during rotorcraft maneuvers.
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公开(公告)号：US20200262549A1
公开(公告)日：2020-08-20
申请号：US16716264
申请日：2019-12-16
Applicant: Textron Innovations Inc.
Abstract: An advancing blade concept rotorcraft includes an airframe and a pylon assembly subject to vibration. The pylon assembly includes a dual rotor system having coaxially disposed top and bottom rotor assemblies that counter rotate relative to one another. The advancing blade concept rotorcraft includes a vibration isolation system including at least one pylon link coupled to the airframe and the pylon assembly. The pylon link includes a Liquid Inertia Vibration Eliminator unit operable to reduce transmission of the pylon assembly vibration to the airframe. The advancing blade concept rotorcraft includes active force generators adjacent to the pylon assembly. The active force generators include a first active force generator producing a force in a first direction and a second active force generator producing a force in a second direction to counteract multidirectional oscillations of the pylon assembly, thereby reducing vibration of the advancing blade concept rotorcraft.
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公开(公告)号：US10974822B2
公开(公告)日：2021-04-13
申请号：US16169745
申请日：2018-10-24
Applicant: Textron Innovations Inc.
Inventor： Michael Reaugh Smith , Jouyoung Jason Choi
Abstract: An anti-tail buffet device leverages existing rotorcraft components to attenuate a tailboom's lateral “ringing” from air buffeting. Anti-buffet masses are tuned to the tailboom's lateral-bending or torsional natural frequency such that when lateral motion occurs, the response at this frequency is cancelled by the anti-buffet system, preventing this vibration from entering into the tailboom structure. Motion stops prevent over-travel. The mass of the tail rotor actuator is soft-mounted, such that its natural frequency is equal to the tailboom's lateral-bending or torsional natural frequency. When lateral loading occurs on the tail rotor disk, the lateral response at this frequency is attenuated by the soft-mounted tail rotor actuator, thereby preventing the vibration in the tailboom structure.
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Patent Agency Ranking
公开(公告)号：US11932380B2
公开(公告)日：2024-03-19
申请号：US17154925
申请日：2021-01-21
Applicant: Textron Innovations Inc.
Inventor： Frank Bradley Stamps , Michael Reaugh Smith , Bradley Joseph Passe
IPC: B64C27/22 , B64C27/00 , B64C27/10 , B64C27/26 , F16F15/167
CPC classification number: B64C27/001 , B64C27/10 , B64C27/22 , B64C27/26 , F16F15/167 , B64C2027/002 , F16F2222/08 , F16F2228/066 , F16F2230/18
Abstract: A compound helicopter includes a fuselage including a fuselage airframe, a translational thrust system coupled to the fuselage airframe and a pylon assembly subject to vibration. The pylon assembly includes a transmission and a rotor system having a main rotor assembly. The compound helicopter also includes a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency. Each augmented liquid inertia vibration eliminator unit includes at least one active tuning element movable to tune the isolation frequency thereof.
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公开(公告)号：US11603207B2
公开(公告)日：2023-03-14
申请号：US16721000
申请日：2019-12-19
Applicant: Textron Innovations Inc.
Inventor： Daniel Frank Devitt , Michael Reaugh Smith
Abstract: In some implementations, in an emergency in the vehicle, an emergency evacuation path is illuminated using the light emitted from the emergency evacuation rope where at least a portion of the emergency evacuation path extends to a location outside the vehicle. Egress of occupants along the emergency evacuation path is enabled using an emergency evacuation rope.
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公开(公告)号：US11214362B2
公开(公告)日：2022-01-04
申请号：US16716264
申请日：2019-12-16
Applicant: Textron Innovations Inc.
Abstract: An advancing blade concept rotorcraft includes an airframe and a pylon assembly subject to vibration. The pylon assembly includes a dual rotor system having coaxially disposed top and bottom rotor assemblies that counter rotate relative to one another. The advancing blade concept rotorcraft includes a vibration isolation system including at least one pylon link coupled to the airframe and the pylon assembly. The pylon link includes a Liquid Inertia Vibration Eliminator unit operable to reduce transmission of the pylon assembly vibration to the airframe. The advancing blade concept rotorcraft includes active force generators adjacent to the pylon assembly. The active force generators include a first active force generator producing a force in a first direction and a second active force generator producing a force in a second direction to counteract multidirectional oscillations of the pylon assembly, thereby reducing vibration of the advancing blade concept rotorcraft.
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公开(公告)号：US11142334B2
公开(公告)日：2021-10-12
申请号：US15846783
申请日：2017-12-19
Applicant: Textron Innovations Inc.
Inventor： Cheng-Ho Tho , Michael Reaugh Smith
Abstract: An in-flight impact protection system for aircraft. An aircraft having a panel, with a sensor disposed on the aircraft and adapted to transmit a signal and receive a reflection of the signal. A controller coupled to the sensor and adapted to receive the reflection from the sensor to determine whether an object is near the aircraft's panel. An inflation device, which includes a tube member, is coupled to the controller and positioned inside the aircraft, proximate the panel. After determining that the object is near the panel, the controller can activate the inflation device so that the tube member inflates, thereby buttressing at least a portion of the panel. The panel can be a windshield, fuselage member, or other suitable component.
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公开(公告)号：US11131363B2
公开(公告)日：2021-09-28
申请号：US15785114
申请日：2017-10-16
Applicant: Textron Innovations Inc.
Inventor： Michael Reaugh Smith , Frank Bradley Stamps , Craig Turner , Maurice Griffin
Abstract: A vibration attenuating fluid mount with a partitioned compensator includes an inner member, an outer member, a flexible member having a castellated transition between a fluid passageway and at least one operating chamber. A membrane may be disposed in a volume compensator in fluid communication with one or more operating chambers. The inner member and outer member may be connected via a castellated connection, a swaged lock ring, or a split-lock ring.
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