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公开(公告)号：US20200298967A1
公开(公告)日：2020-09-24
申请号：US16360803
申请日：2019-03-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Reaugh Smith , Jouyoung Jason Choi , Joseph Richard Carpenter , Steve Michael Loveland
IPC: B64C27/00
Abstract: In some examples, an aircraft comprises an airframe, a rotor system coupled to the airframe, and a vibration attenuation system. The rotor system is operable to exert a vibratory force on the airframe. The vibration attenuation system comprises two or more batteries and elastic devices. The two or more batteries are operable to supply power to the rotor system. The elastic devices coupled to the two or more batteries and the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries. In other examples, a method comprises coupling elastic devices to two or more batteries and an airframe of an aircraft. The elastic devices receiving a vibratory force via the airframe and attenuate the vibratory force based on facilitating oscillation of the two or more batteries.
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公开(公告)号：US11097836B2
公开(公告)日：2021-08-24
申请号：US16360803
申请日：2019-03-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Reaugh Smith , Jouyoung Jason Choi , Joseph Richard Carpenter , Steve Michael Loveland
IPC: B64C27/00
Abstract: In some examples, an aircraft comprises an airframe, a rotor system coupled to the airframe, and a vibration attenuation system. The rotor system is operable to exert a vibratory force on the airframe. The vibration attenuation system comprises two or more batteries and elastic devices. The two or more batteries are operable to supply power to the rotor system. The elastic devices coupled to the two or more batteries and the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries. In other examples, a method comprises coupling elastic devices to two or more batteries and an airframe of an aircraft. The elastic devices receiving a vibratory force via the airframe and attenuate the vibratory force based on facilitating oscillation of the two or more batteries.
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公开(公告)号：US10752335B2
公开(公告)日：2020-08-25
申请号：US15886655
申请日：2018-02-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Reaugh Smith
Abstract: An emergency escape window for a rotorcraft includes a window frame, a window pane set inside the window frame, a plurality of pins connecting the window frame to the fuselage of the rotorcraft, and a release mechanism having at least one actuator connected to a respective pin and constructed to retract the pin from the window frame. The escape window can then be pivoted away and/or completely detached from the fuselage in the event of an emergency to allow occupants to safely exit the rotorcraft. The disclosure also relate to a method of operating an emergency escape window for a rotorcraft and to a rotorcraft having an emergency escape window.
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公开(公告)号：US10556696B2
公开(公告)日：2020-02-11
申请号：US15249046
申请日：2016-08-26
Applicant: Bell Helicopter Textron 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：US20190113098A1
公开(公告)日：2019-04-18
申请号：US15785114
申请日：2017-10-16
Applicant: Bell Helicopter Textron 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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Patent Agency Ranking
公开(公告)号：US10196151B2
公开(公告)日：2019-02-05
申请号：US15144179
申请日：2016-05-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Martin Peryea , Michael Reaugh Smith , Douglas Hamelwright, Jr. , Albert G. Brand , Nicholas J. Plagianos , Joshua Emrich , Timothy Carr
Abstract: A rotorcraft includes a fuselage having a fuel tank receiving assembly with a fuel tank positioned therein. The fuel tank including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank forming a restraint assembly. The network of straps includes at least one perimeter strap extending at least partially about at least two fuel bags and at least one surrounding strap extending at least partially about the at least two fuel bags. The at least one perimeter strap has at least two intersections with the at least one surrounding strap.
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公开(公告)号：US20180057178A1
公开(公告)日：2018-03-01
申请号：US15249046
申请日：2016-08-26
Applicant: Bell Helicopter Textron 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：US20170313434A1
公开(公告)日：2017-11-02
申请号：US15144179
申请日：2016-05-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Martin Peryea , Michael Reaugh Smith , Douglas Hamelwright, JR. , Albert G. Brand , Nicholas J. Plagianos , Joshua Emrich , Timothy Carr
Abstract: A rotorcraft includes a fuselage having a fuel tank receiving assembly with a fuel tank positioned therein. The fuel tank including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank forming a restraint assembly. The network of straps includes at least one perimeter strap extending at least partially about at least two fuel bags and at least one surrounding strap extending at least partially about the at least two fuel bags. The at least one perimeter strap has at least two intersections with the at least one surrounding strap.
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公开(公告)号：US20200324883A1
公开(公告)日：2020-10-15
申请号：US16383161
申请日：2019-04-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Reaugh Smith , Frank B. Stamps , David E. Heverly, II
IPC: B64C27/00 , F16F7/10 , F16F13/26 , F16F13/22 , F16F15/027
Abstract: In some examples, an oscillatory pumping system comprises: one or more active piston, a fluid, and two motors. The one or more active piston is disposed in a channel fluidically coupling two fluid chambers. The passive piston has a frequency response operable to counteract a vibratory displacement. The fluid is disposed in the channel and the two fluid chambers. The two motors couple to the one or more active piston. The two motors are operable to selectively change the frequency response of the passive piston based on oscillating the one or more active piston.
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公开(公告)号：US10386858B2
公开(公告)日：2019-08-20
申请号：US15594393
申请日：2017-05-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Mike Bothwell , Jillian Samantha Alfred , Sung Kyun Kim , Marko Vuga , Matthew Hendricks , Mark Wasikowski , Thomas Parham , Michael Reaugh Smith
Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft, filtering the measured yaw rate or the measured lateral acceleration using a filter to form a filtered measured yaw rate or a filtered measured lateral acceleration, and regulating a yaw rate or a lateral acceleration of the rotorcraft based on the measured yaw rate or the measured lateral acceleration. The filter includes a bandpass characteristic or a notch characteristic, and the filtering is configured to reduce lateral vibrations caused by airflow in a tail section of the rotorcraft.
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