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公开(公告)号：US11565798B2
公开(公告)日：2023-01-31
申请号：US17322053
申请日：2021-05-17
发明人： Peter Sharpe
IPC分类号： B64C25/00 , B64C25/62 , B64C25/60 , F15B11/12 , F16F9/088 , F15B1/10 , B64C25/34 , F16F9/52 , F16F9/06
摘要： A center biased actuator having an outer cylinder, a slave cylinder linearly transposed within the outer cylinder, a rod assembly with a piston linearly transposed within the slave cylinder and a rod extending from the outer cylinder, one or more first dynamic seals arranged to act on a sidewall of the rod to inhibit hydraulic fluid leaking from the outer cylinder, one or more second dynamic seals arranged to act on a sidewall of the slave cylinder or an inner surface of the outer cylinder to inhibit hydraulic fluid leaking from the outer cylinder, and a gas chamber comprising a sealed expandable chamber containing gas. The expandable chamber is arranged to act on hydraulic fluid within the center biased actuator to bias the center biased actuator to assume an intermediate condition which lies between a compressed condition and an extended condition.
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公开(公告)号：US11091251B2
公开(公告)日：2021-08-17
申请号：US16197831
申请日：2018-11-21
发明人： Richard Brandler
摘要： A shock strut includes a first piston having a first hollow interior and a second piston having a second hollow interior. The first piston is movably mounted to the second piston. The shock strut additionally includes a housing having a third hollow interior, and the second piston is movably mounted to the housing. In response to application of a force to the shock strut, the first piston is receivable within the second piston during a first stage of compression and together, the first piston and the second piston are receivable within the housing during a second stage of compression.
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公开(公告)号：US20200377202A1
公开(公告)日：2020-12-03
申请号：US16426357
申请日：2019-05-30
申请人： CTLP, LLC
摘要： A main landing gear assembly for an aircraft has an upper beam and a lower beam. The proximal ends of the upper and lower beams are each connected to a trunnion assembly that is mounted on the fuselage or wing of the aircraft. The distal ends of the upper and lower beams are each affixed to an axel support structure on which a main wheel of the landing gear assembly is mounted. In the gear assembly, the upper beam and the lower beam are coplanar and act together, in combination, to accommodate a planar flexure of the gear assembly during aircraft takeoffs and landings.
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公开(公告)号：US20200346743A1
公开(公告)日：2020-11-05
申请号：US16400002
申请日：2019-04-30
申请人： Bell Textron Inc.
发明人： Guy Bernard
摘要： An energy absorbing landing system for an aircraft having a fuselage includes landing legs rotatably coupled to the fuselage configured to outwardly rotate when receiving a landing load having a magnitude. The energy absorbing landing system also includes an energy absorption unit coupled to the fuselage and cables coupling the energy absorption unit to the landing legs. The energy absorption unit is configured to selectively apply a resistance to the outward rotation of the landing legs via the cables based on the magnitude of the landing load, thereby absorbing the landing load when the aircraft lands.
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95.发明授权公开(公告)号：US10589848B2
公开(公告)日：2020-03-17
申请号：US15395058
申请日：2016-12-30
摘要： A landing-gear assembly (1) for an aircraft, the landing-gear assembly comprising: an axle shaft (2); a leg (3) presenting a first portion (3a) carrying said axle shaft (2) and a second portion (3b) connected to a carrier structure of the aircraft; a main damper (5); and a first secondary damper (6a) distinct from the main damper (5). The first secondary damper (6a) is carried by the axle shaft (2) and comprises: an inertial mass (M); and connection means (7a) between the inertial mass (M) and the axle shaft (2) damping movements of the inertial mass (M) along a first axis (X1) of movement of the inertial mass (M) relative to the axle shaft (2), said first axis of movement (X1) extending in a plane (P) perpendicular to said steering axis (Z).
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公开(公告)号：US20190185145A1
公开(公告)日：2019-06-20
申请号：US16221948
申请日：2018-12-17
发明人： Neil Richard Price
CPC分类号： B64C25/22 , B64C25/10 , B64C25/12 , B64C25/26 , B64C25/62 , F16F1/025 , F16F1/027 , F16F13/00
摘要： An aircraft landing gear assembly includes a bi-stable, split line tube biased to assume a tubular condition to serve in place of a lock link or side stay and a flexible vessel actuator configured to radially enlarge the tube at a region for folding.
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公开(公告)号：US20190144105A1
公开(公告)日：2019-05-16
申请号：US16189073
申请日：2018-11-13
发明人： Peter Sharpe
摘要： A center biased actuator having an outer cylinder, a slave cylinder linearly transposed within the outer cylinder, a rod assembly with a piston linearly transposed within the slave cylinder and a rod extending from the outer cylinder, one or more first dynamic seals arranged to act on a sidewall of the rod to inhibit hydraulic fluid leaking from the outer cylinder, one or more second dynamic seals arranged to act on a sidewall of the slave cylinder or an inner surface of the outer cylinder to inhibit hydraulic fluid leaking from the outer cylinder, and a gas chamber comprising a sealed expandable chamber containing gas. The expandable chamber is arranged to act on hydraulic fluid within the center biased actuator to bias the center biased actuator to assume an intermediate condition which lies between a compressed condition and an extended condition.
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公开(公告)号：US09926072B2
公开(公告)日：2018-03-27
申请号：US14868811
申请日：2015-09-29
发明人： Mark Collins , Marcin Chilik
IPC分类号： B64C25/22 , B22F3/24 , B64C25/00 , B64C25/18 , B64C25/60 , B64C25/62 , B33Y40/00 , B22F7/06 , B22F3/105 , B33Y10/00 , B33Y80/00
CPC分类号： B64C25/22 , B22F3/1055 , B22F3/24 , B22F7/06 , B22F2998/10 , B33Y10/00 , B33Y40/00 , B33Y80/00 , B64C25/00 , B64C25/18 , B64C25/60 , B64C25/62 , Y02P10/295 , B22F2003/247
摘要： A method of forming an aerospace component, the method including: forming a first subcomponent by an additive layer manufacturing (ALM) process, the first subcomponent having an inner surface defining an inner space; performing a non-ALM machining process to modify a portion of the inner surface of the first subcomponent; and forming a second subcomponent by an ALM process, the second subcomponent being arranged to close the inner space to complete the component.
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公开(公告)号：US20170349270A1
公开(公告)日：2017-12-07
申请号：US15608544
申请日：2017-05-30
发明人： Yann Simonneaux , Jon Smith
CPC分类号： B64C25/62 , B64C25/60 , B64F5/60 , F16F9/0245 , G01D5/2291 , G05B19/04
摘要： A method for pressurizing and depressurizing a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurization level of a shock absorber. As such, the shock absorber may be pressurized to the correct level without applying an iterative approach, greatly reducing initialization time.
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公开(公告)号：US20170217574A1
公开(公告)日：2017-08-03
申请号：US15238110
申请日：2016-08-16
申请人： Daniel Roger Dufault
发明人： Daniel Roger Dufault
摘要： A reciprocating shock absorber combined with a coil spring are interposed between the fuselage of an aircraft and the tail wheel. When the tail wheel engages the runway, its attachment pivots, thereby compressing the shock absorber and the coil spring. This results in smooth transfer of forces from the tail wheel to the fuselage and to the pilot and passengers. If desired, one or more tension springs may counteract the forces imposed by the coil spring to restore the extended configuration of the coil spring and shock absorber.
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