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公开(公告)号：US11820184B2
公开(公告)日：2023-11-21
申请号：US16936016
申请日：2020-07-22
申请人： SUBARU CORPORATION
摘要： A land-and-air vehicle configured to switch between a ground traveling mode and an aerial flight mode incudes a body, a wing, a wheel, a suspension, and a lock mechanism. The wing is attached to the body. The wheel is provided on a lower side of the body. The suspension is configured to support the body via the wheel on ground, and to contract due to self-weight of the land-and-air vehicle. The lock mechanism is configured to limit expansion of the suspension from a state in which the suspension has contracted due to the self-weight.
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公开(公告)号：US11753151B2
公开(公告)日：2023-09-12
申请号：US17736787
申请日：2022-05-04
发明人： David Marles
摘要： A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.
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公开(公告)号：US11603187B2
公开(公告)日：2023-03-14
申请号：US16264439
申请日：2019-01-31
申请人： The Boeing Company
发明人： Katie M Plain , Kristina R Mauger
摘要： Systems and methods are provided for door alignment of an aircraft landing gear door. One embodiment is an apparatus that includes a plurality of adjustable rods configured to temporarily install in an aircraft to stand in place of a final adjustable part, each of the adjustable rods configured to position a block for stopping a door of the aircraft. Each of the adjustable rods includes a telescopic body configured to extend and retract in length, and a spring configured to compress to reduce the length of the telescopic body, and to expand to extend the length of the telescopic body. Each adjustable rod also includes a locking mechanism configured to lock the telescopic body at a fixed length to prevent expansion of the spring, and to unlock the telescopic body to release the spring and adjust the telescopic body to an adjusted length.
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公开(公告)号：US20220219811A1
公开(公告)日：2022-07-14
申请号：US17541181
申请日：2021-12-02
申请人： The Boeing Company
发明人： Sean C. Webb
IPC分类号： B64C25/16
摘要： A landing gear door system for a landing gear compartment includes a door pivotable about a pivot pin configured for disposition in a longitudinal direction on an airframe, and a mechanism configured to rotate the door about the pivot pin between a closed position, in which an outer surface of the door panel is configured to provide aerodynamic continuity with an outer aircraft skin of the airframe, and an open position, in which the door is rotated into the landing gear compartment and an opening is exposed. The door has a door panel rigidly connected with an arm such that the door panel and arm generally form a V-shape as viewed in the longitudinal direction.
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公开(公告)号：US20220194564A1
公开(公告)日：2022-06-23
申请号：US17604272
申请日：2020-08-25
发明人： Paul L'ALLIER , Andy MOUNTY , Sean KERR
IPC分类号： B64C25/22 , B64C25/16 , F15B11/024 , F15B15/18
摘要： An aircraft hydraulic actuation system for retracting an aircraft landing gear. The actuation system includes a supply line arranged to carry hydraulic fluid pressurized by a pump, a return line arranged to return hydraulic fluid to a reservoir, and a hydraulic actuator 128. In a first mode of operation, a first chamber 130 of the actuator 128 is supplied with pressurized hydraulic fluid from the supply line such that a piston 134 is moved in a first direction so as to move a load such as a landing gear. In a second mode of operation, the first chamber 130 is taken out of fluid communication with the supply line and a second chamber 132 is in fluid communication with the return line, such that the piston 134 is able to be moved under the influence of the load, for example when the landing gear extends under gravity.
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公开(公告)号：US11338938B2
公开(公告)日：2022-05-24
申请号：US16734773
申请日：2020-01-06
申请人： The Boeing Company
发明人： Chad R. Adamson
摘要： A factory for assembling aircraft or other systems includes a factory floor with multiple build stations. The factory floor includes a hub-and-spoke tool track having radial track sections connected to and extending radially from a circular center hub section. Each track section terminates at a respective build station. A mobile transport travels along the track to the build stations, transforms into different join tools at a predetermined build station, and thereafter engages and supports the components. An overhead crane may perform another task at each build station. The factory floor may include a first floor positioned below a smaller diameter second floor with ramps interconnecting the floors. A center tower is surrounded by the floor(s), with the center tower defining rooms. An aircraft may be assembled via a method using the above-noted factory.
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公开(公告)号：US11312482B2
公开(公告)日：2022-04-26
申请号：US16449373
申请日：2019-06-22
发明人： Bruce Bennett Bacon
摘要： A component alignment system for an aircraft includes a first component having a first surface including first shaped projections that repeat in at least two directions along the first surface. The component alignment system also includes a second component having a second surface including second shaped projections that repeat in at least two directions along the second surface. The first shaped projections are complementary to the second shaped projections such that the first surface is translationally and rotationally constrained relative to the second surface when the first and second shaped projections are in an interlocked position.
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公开(公告)号：US20210403145A1
公开(公告)日：2021-12-30
申请号：US17354787
申请日：2021-06-22
发明人： Ladislao LÓPEZ LÓPEZ
摘要： A landing gear door system, including a landing gear bay including an opening and accommodating a landing gear in a retracted position, a landing gear door for opening and closing the opening, an actuator for operating the landing gear door between an open and a closed position, a lock located in the landing gear bay and latching the landing gear door in the closed position, a stop fitting located in the landing gear bay and configured to be in connection with the landing gear door at least in its latched position. The landing gear door system further includes an additional actuator configured to apply a force to the landing gear door in its closed position and to elastically deform the landing gear door towards the landing gear door bay.
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公开(公告)号：US11192638B2
公开(公告)日：2021-12-07
申请号：US16670909
申请日：2019-10-31
发明人： Stéphane Frion
摘要： Shield assemblies for an aircraft landing gear include an aerodynamic shield, a first support bracket assembly, and a second support bracket assembly. The first support bracket assembly is configured to couple with a structural member of the aircraft landing gear, to support a first end of the aerodynamic shield, and to have a first position that is fixed relative to the structural member in an x-direction, a y-direction, and a z-direction. The first support bracket assembly has a first clamp that is configured to fix the first support bracket assembly relative to the structural member in the x-direction. The second support bracket assembly is configured to support a second end of the aerodynamic shield and to have a second position that is fixed relative to the structural member in the y-direction and the z-direction.
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公开(公告)号：US20190039722A1
公开(公告)日：2019-02-07
申请号：US15670566
申请日：2017-08-07
申请人： The Boeing Company
发明人： Eric E. Adamson , David A. Treiber
IPC分类号： B64C25/16
摘要： An exposed main landing gear cavity in a bottom wall of an aircraft fuselage may include a main landing gear cavity outer ring recessed within the fuselage and having an inner surface encircling the main landing gear cavity, first baffle extending inward from the outer ring inner surface at an aft and inboard position on the inner surface, and a second baffle extending inward from the outer ring inner surface at an aft and outboard position on the outer ring inner surface. The main landing gear cavity may further include an aft fairing disposed proximate the outer ring bottom edge of the outer ring and connected to the fuselage at an aft side of the main landing gear cavity. An aft fairing top surface may have curvature causing the top surface to extend downward away from the outer ring as the top surface extends inward away from the outer ring.
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