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公开(公告)号：US10669021B2
公开(公告)日：2020-06-02
申请号：US14022524
申请日：2013-09-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Paul K. Oldroyd , Wei-Yueh Lee , James D. Hethcock, Jr. , John R. McCullough , Patrick R. Tisdale
IPC: B64C27/473 , B64C3/20
Abstract: An airfoil member can have a root end, a tip end, a leading edge, and a trailing edge. The airfoil member can include an upper skin, a lower skin, and a composite core member having a plurality of cells, an upper surface network of the cells can be bonded to the upper skin, a lower surface network of the cells can be bonded to the lower skin. The composite core can have a septum layer embedded in the cells that form the composite core, the septum layer being configured to provide tailored characteristics of the airfoil member.
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公开(公告)号：US20200158181A1
公开(公告)日：2020-05-21
申请号：US16195818
申请日：2018-11-19
Applicant: Bell Helicopter Textron Inc.
IPC: F16D1/08
Abstract: Briefly, implementations of claimed subject matter relate to methods and devices for coupling a first rotating shaft to a second shaft. In a particular implementation, an end of a plurality of resilient fingers of a resilient structure may be radially displaced to permit positioning of the resilient structure over a first shaft. An inwardly-directed portion of each of the plurality of the resilient fingers of the resilient structure may be secured to a channel located on an inner surface of a second shaft. After securing the resilient structure to the second shaft, the one or more resilient fingers of the resilient structure may be positioned within a slotted ladder ring encircling the first shaft.
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公开(公告)号：US20200156803A1
公开(公告)日：2020-05-21
申请号：US15895619
申请日：2018-02-13
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , Greg Alan Whittaker , Bryan Keith Sugg
Abstract: One embodiment is a system comprising fuel tank comprising a pressure vessel for storing fuel for a vehicle, the fuel tank disposed within a fuselage of the vehicle and extending a majority of a length of the fuselage, wherein a center of gravity of the fuel tank is substantially aligned with a center of gravity of the fuselage. The fuel tank may be disposed within the fuselage such that the fuel tank bears at least a portion of a load borne by the fuselage. Alternatively, the fuel tank may be disposed within the fuselage such that the fuel tank is isolated from loads borne by the fuselage. In certain embodiments, the fuel tank comprises a filament wound pressure vessel.
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公开(公告)号：US20200156773A1
公开(公告)日：2020-05-21
申请号：US16197761
申请日：2018-11-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Frank Bradley Stamps , David Heverly , Michael R. Smith , Michael Scott Seifert , Thomas C. Parham, JR. , Gary Miller , Jouyoung Jason Choi , Richard E. Rauber
IPC: B64C27/00
Abstract: A vibration attenuator for an aircraft has first and second coaxial spinners configured for rotation about a mast axis and relative to a rotor. Upper and lower weights of each spinner are spaced radially from the axis and positioned 180 degrees from each other about the axis. The weights of each spinner are spaced from each other a distance parallel to the mast axis, each weight rotating about the mast axis in a different plane. The spinners rotate together relative to the rotor at a selected angular rate and are selectively rotatable relative to each other between a minimum-moment configuration, in which the upper weight of each spinner is angularly aligned with the lower weight of the other spinner, and a maximum-moment configuration, in which the upper weights are angularly aligned and the lower weights are angularly aligned, producing a whirling moment about the mast axis as the spinners rotate.
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公开(公告)号：US10655726B2
公开(公告)日：2020-05-19
申请号：US15729112
申请日：2017-10-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Scott Poster
IPC: F16H57/04 , F16K31/122 , B64C27/12 , F16N7/00
Abstract: A valve with supplemental media and a piston configured to open the valve when a first force is greater than a second force. The pressure of the supplemental media exerts a substantial portion of the first force. The valve also has a biasing member that changes volume as temperature changes and exerts a substantial portion of the second force. The second force decreases as the temperature of the biasing member increases.
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Patent Agency Ranking
公开(公告)号：US20200148369A1
公开(公告)日：2020-05-14
申请号：US16189722
申请日：2018-11-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Nicholas Allen Torske
IPC: B64D15/12
Abstract: Briefly, the disclosure relates to apparatuses and methods to enclose electrical contacts for de-icing equipment utilized on fixed-wing aircraft and rotary-wing aircraft, such as helicopters and tiltrotor aircraft. In some implementations, enclosing electrical contacts for a de-ice heater blanket may ensure that high-quality electrical connections are made between conductors of one or more de-icing cables and the electrical contacts of the de-ice heater blanket. Such high-quality electrical connections may be maintained even during aircraft operations conducted in below-freezing ambient environments, rainy and/or wet environments, dusty desert environments, and so forth.
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公开(公告)号：US20200148345A1
公开(公告)日：2020-05-14
申请号：US16188937
申请日：2018-11-13
Applicant: Bell Helicopter Textron Inc.
Inventor： John Robert Wittmaak, JR. , Russell C. Peters , Andrew Vincent Louis
Abstract: One embodiment is an aircraft including at least one propulsion assembly; a cargo area for receiving payload to be transported by the aircraft; and a control system for determining characteristics of the received payload; automatically determining optimal control gains for operating the aircraft including the payload based on the determined payload characteristics; and providing control signals to at least one of the at least one propulsion assembly and a control assembly of the aircraft to control operation of the at least one propulsion assembly in accordance with the determined optimal control gains.
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公开(公告)号：USD878258S1
公开(公告)日：2020-03-17
申请号：US29675582
申请日：2019-01-03
Applicant: Bell Helicopter Textron Inc.
Designer： James Gibson , Carey Cannon , William Kyle Heironimus
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公开(公告)号：US10589855B2
公开(公告)日：2020-03-17
申请号：US15621686
申请日：2017-06-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk L. Groninga , Daniel B. Robertson
Abstract: In a first aspect, there is a rotor system for a tiltrotor aircraft, the rotor system including an upper outboard engine in a fixed location on a wing member of the tiltrotor aircraft; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position. In another aspect, there is provided a tiltrotor aircraft including a fuselage; a wing member; an upper outboard engine in a fixed location on the wing member; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position.
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公开(公告)号：US20200079038A1
公开(公告)日：2020-03-12
申请号：US16125592
申请日：2018-09-07
Applicant: Bell Helicopter Textron Inc.
Inventor： Sylvain Tessier , Pascal Forget
Abstract: There is disclosed a molding assembly including a mold having a first surface and an opposed second surface. The mold defines a cavity bounded by two side walls converging toward each other from the first surface toward the second surface. Two mandrels are each removably receivable in the cavity and have a first wall, a second wall opposed to the first wall, an inner wall, and an outer wall opposed to the inner wall. The inner walls face each other and define a gap therebetween for receiving a composite material to be cured. The outer walls are angled and each slidably engage a respective one of the two side walls. A method of co-curing a stiffener and a panel is also disclosed.
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