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公开(公告)号：US10816019B2
公开(公告)日：2020-10-27
申请号：US15969413
申请日：2018-05-02
Applicant: THE BOEING COMPANY
Inventor： Matthew D. Uhlman , Barry D. Hance , Herbert Guttler , Robert J. Hawk , Paul Smith , Patrick Fahey , Ellen A. Pifer , Christopher P. Beamis , Ali Abdelmagid , Patrick McCormick , Mark W. Lesyna
IPC: F15B21/04 , F15B21/042 , B64C13/40 , F15B11/08 , F15B20/00
Abstract: A hydraulic system (e.g., of an aircraft or other vehicle) includes a pump, a pressure line coupled to the pump and configured to distribute pressurized hydraulic fluid, and a return line configured to return hydraulic fluid to a reservoir. The hydraulic system also includes an auxiliary leakage valve coupled to the pressure line, to the return line, and to an actuator. The auxiliary leakage valve is configured to receive a control signal and, based on the control signal, selectively open a restricted fluid path. The restricted fluid path couples the pressure line to the return line to allow a restricted amount of the hydraulic fluid to flow from the pressure line to the return line.
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Patent Agency Ranking
公开(公告)号：US20190338793A1
公开(公告)日：2019-11-07
申请号：US15969413
申请日：2018-05-02
Applicant: THE BOEING COMPANY
Inventor： Matthew D. Uhlman , Barry D. Hance , Herbert Guttler , Robert J. Hawk , Paul Smith , Patrick Fahey , Ellen A. Pifer , Christopher P. Beamis , Ali Abdelmagid , Patrick McCormick , Mark W. Lesyna
Abstract: A hydraulic system (e.g., of an aircraft or other vehicle) includes a pump, a pressure line coupled to the pump and configured to distribute pressurized hydraulic fluid, and a return line configured to return hydraulic fluid to a reservoir. The hydraulic system also includes an auxiliary leakage valve coupled to the pressure line, to the return line, and to an actuator. The auxiliary leakage valve is configured to receive a control signal and, based on the control signal, selectively open a restricted fluid path. The restricted fluid path couples the pressure line to the return line to allow a restricted amount of the hydraulic fluid to flow from the pressure line to the return line.
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公开(公告)号：US20180015996A1
公开(公告)日：2018-01-18
申请号：US15209974
申请日：2016-07-14
Applicant: The Boeing Company
Inventor： Michael P. Shemkunas , Kenneth D. Cominsky , Steven S. Heer , David P. Heck , Benjamin D. Smith , John A. Baumann , Matthew D. Uhlman , Burke L. Reichlinger , Eric E. Thomas , James P. Dobberfuhl
IPC: B64C3/18 , B64C3/26 , C25D11/04 , B23K20/233 , B23K20/12 , B23K103/10 , B23K101/12
CPC classification number: B64C3/18 , B23K20/1265 , B23K20/2336 , B23K2101/12 , B23K2103/10 , B64C3/182 , B64C3/185 , B64C3/20 , B64C3/26 , B64C23/065 , B64F5/10 , C25D11/04 , Y02T50/164
Abstract: Provided are wingtip torque boxes and methods of fabricating such boxes using friction stir welding. Specifically, a wingtip torque box may be formed by friction stir welding two monolithic clamshells along their respective spars thereby forming a new monolithic structure. Use of the friction stir welding and monolithic clamshells simplifies the overall fabrication process and yields a robust wingtip torque box that can be bolted on or otherwise attached to an aircraft wing. The wingtip torque box may include internal grid stiffeners and/or external stiffeners that may be also monolithic with other components of the box. For example, the stiffeners may be machined in spars or skin portions of the clamshells during fabrication of clamshells. The wingtip torque box may have a continuous cavity extending between the ends and, in some embodiments, between spars of the box and providing access for performing various operations inside the box.
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公开(公告)号：US10814983B2
公开(公告)日：2020-10-27
申请号：US15954426
申请日：2018-04-16
Applicant: The Boeing Company
Inventor： Allison M. Feldman , Teresa Jeanna Konopka , Kristen Ann Leenerman , James Emanuel Silva , Matthew D. Uhlman , Luis Rafael Vidal
Abstract: Payload engagement systems, vehicles including the same, and related methods. A payload engagement system includes a vehicle supported portion and a payload mounted portion, one of which includes an insert component, and the other of which includes a receptor component. The payload engagement system is configured to transition between a disengaged configuration and an engaged configuration via rotation of the insert component with respect to the receptor component. In the engaged configuration, the receptor component receives the insert component such that the insert component is rotationally constrained within the receptor component. A method of transporting a payload with a vehicle includes engaging the payload with a payload engagement system that includes a vehicle supported portion and a payload mounted portion, transporting the payload with the vehicle, and disengaging the payload. Each of the engaging and the disengaging includes rotating the vehicle supported portion with respect to the payload mounted portion.
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公开(公告)号：US10479474B2
公开(公告)日：2019-11-19
申请号：US15209974
申请日：2016-07-14
Applicant: The Boeing Company
Inventor： Michael P. Shemkunas , Kenneth D. Cominsky , Steven S. Heer , David P. Heck , Benjamin D. Smith , John A. Baumann , Matthew D. Uhlman , Burke L. Reichlinger , Eric E. Thomas , James P. Dobberfuhl
IPC: B64C3/18 , B23K20/12 , B23K20/233 , B64C3/26 , C25D11/04 , B23K101/12 , B23K103/10
Abstract: Provided are wingtip torque boxes and methods of fabricating such boxes using friction stir welding. Specifically, a wingtip torque box may be formed by friction stir welding two monolithic clamshells along their respective spars thereby forming a new monolithic structure. Use of the friction stir welding and monolithic clamshells simplifies the overall fabrication process and yields a robust wingtip torque box that can be bolted on or otherwise attached to an aircraft wing. The wingtip torque box may include internal grid stiffeners and/or external stiffeners that may be also monolithic with other components of the box. For example, the stiffeners may be machined in spars or skin portions of the clamshells during fabrication of clamshells. The wingtip torque box may have a continuous cavity extending between the ends and, in some embodiments, between spars of the box and providing access for performing various operations inside the box.
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公开(公告)号：US20190315466A1
公开(公告)日：2019-10-17
申请号：US15954426
申请日：2018-04-16
Applicant: The Boeing Company
Inventor： Allison M. Feldman , Teresa Jeanna Konopka , Kristen Ann Leenerman , James Emanuel Silva , Matthew D. Uhlman , Luis Rafael Vidal
Abstract: Payload engagement systems, vehicles including the same, and related methods. A payload engagement system includes a vehicle supported portion and a payload mounted portion, one of which includes an insert component, and the other of which includes a receptor component. The payload engagement system is configured to transition between a disengaged configuration and an engaged configuration via rotation of the insert component with respect to the receptor component. In the engaged configuration, the receptor component receives the insert component such that the insert component is rotationally constrained within the receptor component. A method of transporting a payload with a vehicle includes engaging the payload with a payload engagement system that includes a vehicle supported portion and a payload mounted portion, transporting the payload with the vehicle, and disengaging the payload. Each of the engaging and the disengaging includes rotating the vehicle supported portion with respect to the payload mounted portion.
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