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公开(公告)号：US12097951B2
公开(公告)日：2024-09-24
申请号：US18320346
申请日：2023-05-19
发明人： Benjamin Bishop
摘要： A landing gear assembly is disclosed having a trailing arm for carrying a wheel, a shock absorber pivotally coupled to the arm for damping movement of the arm, and an articulated lock mechanism. The mechanism includes an upper and lower lock links each with a distal end respectively pivotally coupled to the shock and arm. Proximal ends of the lock links are pivotally coupled about a common axis to enable a distance between the distal ends to vary. The mechanism is lockable to lock the assembly in an extended or retracted configuration. When the assembly is in the extended or retracted configuration, the mechanism is locked respectively in an extended or retracted locking configuration, such that the distance between the distal ends of the lock links is substantially the same in either extended or retracted locking configuration.
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公开(公告)号：US20240190559A1
公开(公告)日：2024-06-13
申请号：US18380237
申请日：2023-10-16
申请人： AIRBUS HELICOPTERS
发明人： Roland BECQUET , Benjamin ANSQUER
摘要： A retractable landing gear for an aircraft. The landing gear comprises a rocker arm hinged to a structure of the aircraft and carrying at least one wheel that is able to move between a deployed position and a retracted position, a shock-absorber hinged to the structure, a connecting rod connecting the rocker arm and the shock-absorber, a strut provided with two connecting links that are hinged to each other and respectively hinged to shock-absorber and connected to an actuator fastened to the structure. The connecting rod is out of alignment with the shock-absorber when a force applied to the shock-absorber is less than a predetermined force, and the landing gear comprises a locking device provided with an elastic return member and a stop device for locking the strut when the wheel is in the deployed position, and then for securing the wheel in the deployed position.
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公开(公告)号：US20240182161A1
公开(公告)日：2024-06-06
申请号：US18231709
申请日：2023-08-08
发明人： Axel FINK , Aurelien ACHARD , Didier BERTIN
CPC分类号： B64C25/58 , B64C25/06 , B64C25/34 , B64C2025/325
摘要： A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin device extending laterally from the shock absorber tube and comprising a mounting pin connected to a floor fitting provided at the inner floor.
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公开(公告)号：US20230373650A1
公开(公告)日：2023-11-23
申请号：US17751027
申请日：2022-05-23
发明人： Ross Trevisan
CPC分类号： B64D45/00 , B64C25/58 , B64C25/34 , G01L5/00 , B64D2045/007
摘要： A load detection system detects loads applied to a landing gear assembly during landing. The landing gear assembly includes an axle coupled to a piston rod of a compressible shock strut and a wheel rotatably mounted the axle. A torque link includes a lower link coupled to the piston rod of the shock strut so that compression of the shock strut rotates the link about a first axis. The load detection system includes a probe rotatably coupled about a second axis. The probe engages a ground surface when the shock strut is uncompressed and the wheel contacts the ground surface. The lower link rotates the probe as the shock strut compresses. A sensor senses a position of the probe, which corresponds to a load on the wheel when the shock strut is uncompressed and the wheel is in contact with the ground surface.
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公开(公告)号：US11753153B2
公开(公告)日：2023-09-12
申请号：US17626342
申请日：2020-07-10
IPC分类号： B64C25/58
CPC分类号： B64C25/58
摘要： A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.
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公开(公告)号：US11512738B2
公开(公告)日：2022-11-29
申请号：US16381808
申请日：2019-04-11
申请人： GOODRICH CORPORATION
摘要： A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.
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公开(公告)号：US11338923B2
公开(公告)日：2022-05-24
申请号：US16694705
申请日：2019-11-25
发明人： Matthew Sweeny , Michel Fathallah , Tom Bass , Kranthi Baddam , John R. Foggia
摘要： Disclosed is a technique for landing a drone using a parachute. The technique includes a parachute deployment system (PDS) that can deploy a parachute installed in a drone and land the drone safely. The parachute may be deployed automatically, e.g., in response to a variety of failures such as a free fall, or manually from a base unit operated by a remote user. For example, the PDS can determine the failure of the drone based on data obtained from an accelerometer, a gyroscope, a magnetometer and a barometer of the drone and automatically deploy the parachute if any failure is determined. In another example, the remote user can “kill” the drone, that is, cut off the power supply to the drone and deploy the parachute by activating an onboard “kill” switch from the base unit.
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公开(公告)号：US11248678B2
公开(公告)日：2022-02-15
申请号：US16856601
申请日：2020-04-23
申请人： Goodrich Corporation
发明人： Amir Fazeli , Adnan Cepic , Susanne Reber
摘要： A method for weight off wheel shock strut servicing includes deflating the shock strut, compressing the shock strut via a jack until the shock strut is in a compressed position, charging the shock strut with an oil until a pressure of the oil reduces a volume of a residual air located inside of the shock strut, lowering the jack until a shock strut piston reaches a pre-determined extension, and charging the shock strut with a gas until the gas comprises a pre-determined pressure.
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公开(公告)号：US11235863B2
公开(公告)日：2022-02-01
申请号：US16533626
申请日：2019-08-06
申请人： GOODRICH CORPORATION
发明人： Adam J. Ditzler
摘要： A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes a collar coupled to a brace linkage and the piston, a torque arm configured to resist rotation between the collar and the piston, and a shrink linkage coupled between the torque arm and the cylinder. The collar rotates relative to the cylinder in response to retraction of the landing gear. Rotation of the collar rotates the piston and the torque arm relative to the cylinder. The rotation of the collar relative to the cylinder forces, via the shrink linkage, the piston towards the aircraft attachment within the cylinder.
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公开(公告)号：US11091250B2
公开(公告)日：2021-08-17
申请号：US16117823
申请日：2018-08-30
发明人： Matthew Hilliard
IPC分类号： B64C25/60 , F15B15/14 , F16F9/36 , B64C25/58 , F16C29/02 , F16C33/04 , F16F9/32 , F16F9/34 , F16F9/06
摘要： A telescopic device having a housing and a rod is slidably mounted within a bore of the housing. First and second bearings provide sliding engagement between the rod and the housing. The first bearing is mounted relatively close to the open end of the bore and the second bearing is mounted relatively far from the open end of the bore relative to the first bearing. The second bearing is annular in shape with a central axis, the bearing has a radially outer mounting surface of arcuate cross-section and a radially inner bearing surface for sliding engagement with an outer surface of the rod and wherein the inner sidewall is provided with an annular groove having a second mounting surface of arcuate cross-section to house and retain the second bearing.
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