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公开(公告)号：US4061295A
公开(公告)日：1977-12-06
申请号：US642788
申请日：1975-12-22
申请人： Paul T. Somm
发明人： Paul T. Somm
摘要： The damping coefficient and spring constant of shock absorbing struts for commercial jet aircraft landing gears are selected to allow optimum absorption of forces on the landing gears at touchdown for an aircraft that has been descending at the maximum permissible "sinkrate" (descent rate immediately prior to touchdown). When so selected, the shock absorbing struts are unable to effectively dampen vertical oscillations of the aircraft body ensuing from a downward plunging of the weight of the aircraft due to the deployment of lift spoilers immediately after touchdown. To rapidly attenuate these post-touchdown vertical oscillations (for more efficient braking and ground handling), while still affording the proper spring constant and damping coefficient necessary for absorbing touchdown impact forces at maximum "sinkrate", the damping of each shock strut is substantially increased after the first cycle of strut compression and re-extension by automatically sensing the occurrence of touchdown, and after a predetermined time delay therefrom, actuating a damping control within each shock strut, to change the damping coefficient to an increased level.
摘要翻译： 选择商用喷气飞机起落架的减震支柱的阻尼系数和弹簧常数，以便在已达到最大允许“下沉速度”（下降率在 接地）。 当这样选择时，由于在触地之后立即部署升降机，因此减震支柱不能有效地抑制飞机机身的垂直振动，从而导致飞机重量的向下倾斜。 为了快速衰减这些接地后垂直振荡（为了更有效的制动和地面处理），同时仍然提供适当的弹簧常数和阻尼系数，以便在最大“下沉”处吸收触地冲击力，每个冲击支柱的阻尼大大增加 在通过自动感测触地发生的第一次循环的支柱压缩和再延伸之后，并且在经过预定的时间延迟之后，启动每个冲击支柱内的阻尼控制，以将阻尼系数改变到增加的水平。
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公开(公告)号：US4011929A
公开(公告)日：1977-03-15
申请号：US573827
申请日：1975-05-02
CPC分类号： F16F7/01
摘要： There is provided a new improved dampening medium for a shock dampening device. The dampening device comprises a closed chamber, a movable piston rod extending through the chamber and an enlarged piston head located on the piston rod. Located in the interior space of the closed chamber under pressure is a compressible solid, fragmented, particulate mass of cured unfilled silicone rubber composition for producing a damping effect on the piston rod and head. The damper device includes a threaded plug for varying the internal static pressure on the compressible mass within the chamber and apertures extending through the piston head or an annular space between the outer edge of the piston head and the interior of the chamber for bypassing the compressible mass.
摘要翻译： 提供了一种用于冲击阻尼装置的新的改进的阻尼介质。 阻尼装置包括封闭室，延伸穿过室的可移动活塞杆和位于活塞杆上的增大的活塞头。 位于封闭室的内部空间内的压力是可固化的，碎片的，固化的未填充的硅橡胶组合物的颗粒物质，用于在活塞杆和头部上产生阻尼作用。 阻尼器装置包括用于改变腔室内的可压缩物质上的内部静压力的螺纹塞子，以及延伸穿过活塞头部的孔或活塞头的外边缘与腔室内部之间的环形空间，用于绕过可压缩质量块 。
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公开(公告)号：US3559925A
公开(公告)日：1971-02-02
申请号：US3559925D
申请日：1968-08-20
CPC分类号： B64C25/34
摘要： In main undercarriage gear for an aircraft, in which the wheels are in two pairs in tandem, one pair being forward of the lower end of the main undercarriage strut and the other pair being rearward, a configuration is provided to enable either one, or both, pairs of wheels to castor when the aircraft is taxiing so as to avoid tyre scrub. The pair of wheels which is to castor is mounted in trailing configuration on the subsidiary leg which is itself carried on the main strut by means of a parallel linkage so that it can rise and fall with respect to the main strut. The wheel pair castors about the vertical axis of this subsidiary leg.
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公开(公告)号：US20240317391A1
公开(公告)日：2024-09-26
申请号：US18388503
申请日：2023-11-09
发明人： Kye Yoon Kim , Choung Hyoung Kim
摘要： The present disclosure relates to a skid device for aircraft and a method for controlling the same that may implement an optimal soft landing even under varied landing conditions in various environments, and the skid device may include: at least one support leg having a hollow portion and fixed to a lower portion of a fuselage; a skid connected to an end of the support leg; a magnetic field generator installed in the hollow portion; and a magnetorheological material accommodated in the hollow portion.
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公开(公告)号：US20240295251A1
公开(公告)日：2024-09-05
申请号：US18590458
申请日：2024-02-28
CPC分类号： F16F9/49 , B64C25/58 , F16F2222/126 , F16F2230/16
摘要： A gas backflow restrictor system as part of an aircraft strut includes the strut defining an inner volume having a first chamber and a second chamber; an orifice plate positioned within the inner volume and separating the first chamber and the second chamber; a standpipe attached to the orifice plate and extending longitudinally within the inner volume, the standpipe having openings extending through a thickness of a wall forming the standpipe, the standpipe further defining an inner channel; and a restrictor mounted within the inner channel, the restrictor having a shelf extending into the inner channel and forming a central opening; the shelf is to reduce gaseous flow through one or more of the openings of the standpipe and toward the orifice plate.
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公开(公告)号：US20240294251A1
公开(公告)日：2024-09-05
申请号：US18509696
申请日：2023-11-15
发明人： Axel FINK , Reynaldo OIOLI-NETO
CPC分类号： B64C25/36 , B64C25/06 , B64C25/58 , B64C2025/325
摘要： A rotorcraft comprising a fuselage forming at least one lower lateral fuselage compartment with at least a first fitting, a second fitting, and a third fitting; and at least one non-retractable wheel-type landing gear that comprises: at least one wheel; a shock absorber with a shock absorber tube having an open end and an axially opposed closed end, and a shock absorber rod telescopically mounted to the shock absorber tube via the open end; a first fixation provided close to the open end on the shock absorber tube and connected to the first fitting; a second fixation provided close to the closed end on the shock absorber tube and connected to the second fitting; and a third fixation provided close to the closed end on the shock absorber tube and connected to the third fitting.
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公开(公告)号：US20240182160A1
公开(公告)日：2024-06-06
申请号：US18233637
申请日：2023-08-14
发明人： Axel FINK , Aurelien ACHARD , Didier BERTIN
CPC分类号： B64C25/36 , B64C25/58 , 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 extending from the shock absorber tube toward a floor fitting provided at the inner floor, wherein the mounting pin is connected to the floor fitting.
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公开(公告)号：US20240140594A1
公开(公告)日：2024-05-02
申请号：US18049941
申请日：2022-10-26
发明人： Michael SACCOCCIA
摘要： A landing gear assembly for a vehicle, such as a helicopter, includes a linkage coupled to the vehicle and configured to reciprocate between a stowed position and a deployed position. A shock strut forms a part of the linkage. The landing gear assembly further includes a side brace having a first end coupled to the linkage and a second end coupled to the vehicle. The side brace provides a driving force that reciprocates the linkage between the stowed and deployed position. The side brace includes an energy attenuation system that dissipates energy when a compressive load on the side brace exceeds a predetermined threshold.
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公开(公告)号：US20230373615A1
公开(公告)日：2023-11-23
申请号：US18320443
申请日：2023-05-19
发明人： Benjamin BISHOP
摘要： An aircraft landing gear assembly is disclosed including a leg assembly having a trailing arm configured to rotate about an axis and carry a wheel, a shock absorber coupled to the arm and enabled to dampen rotation of the arm about the axis within a normal operating range, and to limit the rotation of the arm about the first trailing arm axis to the normal operating range, and a fuse member coupled to the shock absorber. The fuse member is configured to fail in the event a vertical load on the wheel exceeds a pre-determined threshold, wherein failure of the fuse member allows the first trailing arm to rotate about the first trailing arm axis beyond the normal operating range.
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公开(公告)号：US11814160B2
公开(公告)日：2023-11-14
申请号：US17134427
申请日：2020-12-27
申请人： GOODRICH CORPORATION
发明人： Basavaraj Bodki , Hemanth Nagaraja , Steve Healey
CPC分类号： B64C25/60 , F16F9/19 , F16F9/365 , F16F9/3292 , F16F2222/12
摘要： A shock strut is disclosed. The shock strut may include a shock strut cylinder, a shock strut piston that is slidably disposed within the shock strut cylinder, a metering pin, and a percolation seal configured to restrict a flow of liquid between the shock strut cylinder and the shock strut piston.
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