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公开(公告)号：US09878727B2
公开(公告)日：2018-01-30
申请号：US14971350
申请日：2015-12-16
发明人： Anton Gaile
摘要： A rail vehicle spring system has a spring strut, arranged between a bogie and carriage body of the rail vehicle, and includes a cylinder and a piston in the cylinder. Piston spaces are defined below and above the piston head. The piston or the cylinder is connectable with the bogie, while the other component is connectable with the carriage body. A spring cushions the body relative to the bogie, and a hydraulic system is connected with at least one of the piston spaces to charge the space with hydraulic medium. The spring surrounds the cylinder and is contracted by the piston when an excess pressure exists in the lower piston space with respect to the upper piston space, and an entraining element is adjoined by the spring. Only when an excess pressure exists in the lower piston space does the piston rod exerts a force on the entraining element.
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公开(公告)号：US11767101B2
公开(公告)日：2023-09-26
申请号：US17453589
申请日：2021-11-04
发明人： Tobias Roeben , Thomas Sauterleute , Anton Gaile
CPC分类号： B64C13/504 , B64C13/341 , B64C13/40 , B64C13/50 , F15B13/0401 , F15B13/0435 , F15B21/087 , F15B2013/0409 , F15B2211/6656
摘要： The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.
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公开(公告)号：US11292584B2
公开(公告)日：2022-04-05
申请号：US16687716
申请日：2019-11-19
发明人： Frederick Bassett , Anton Gaile
IPC分类号： B64C13/28 , F16D41/066 , F16D7/08 , F16D43/206 , F16D41/06
摘要： The present invention relates to a coupling arrangement for a driving device, wherein the coupling arrangement comprises an input, an output and a coupling, wherein the coupling is non-rotatably connected with the input or with the output, wherein the coupling furthermore comprises torque transmission means which in the coupled condition are configured to connect the output with the input for transmitting a torque from the input to the output, wherein upon exceedance of a torque threshold value in a first operating condition the torque transmission means are arranged such that the input is periodically separated from and connected with the output, and that when the torque threshold value is not reached in a second operating condition, the torque transmission means are arranged such that the input is permanently connected with the output for transmitting a torque.
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公开(公告)号：US20220144414A1
公开(公告)日：2022-05-12
申请号：US17453589
申请日：2021-11-04
发明人： Tobias Roeben , Thomas Sauterleute , Anton Gaile
IPC分类号： B64C13/50 , B64C13/28 , F15B13/043 , F15B13/04
摘要： The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.
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公开(公告)号：US11274712B2
公开(公告)日：2022-03-15
申请号：US16021150
申请日：2018-06-28
发明人： Habib Stegmann , Boris Schweitzer , Anton Gaile
IPC分类号： F16D43/206 , B64C13/28 , F16D7/08
摘要： The invention relates to an overload clutch for a drive gear mechanism for driving components of an aircraft wing, in particular for driving an outer slat flap of an aircraft wing, with at least one driving and at least one driven clutch body and with at least one torque transmission body arranged therebetween. The invention further relates to a drive gear mechanism with a corresponding overload clutch.
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公开(公告)号：US20190010996A1
公开(公告)日：2019-01-10
申请号：US16021150
申请日：2018-06-28
发明人： Habib STEGMANN , Boris Schweitzer , Anton Gaile
IPC分类号： F16D43/206 , B64C13/28
摘要： The invention relates to an overload clutch for a drive gear mechanism for driving components of an aircraft wing, in particular for driving an outer slat flap of an aircraft wing, with at least one driving and at least one driven clutch body and with at least one torque transmission body arranged therebetween. The invention further relates to a drive gear mechanism with a corresponding overload clutch.
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公开(公告)号：US20130221253A1
公开(公告)日：2013-08-29
申请号：US13766080
申请日：2013-02-13
发明人： Joern Frick , Anton Gaile , Franz Weixler
IPC分类号： F16K31/42
CPC分类号： F16K31/42 , F15B13/0402 , F15B13/0433
摘要： The invention relates to a servo valve, in particular a two-stage or multistage electrohydraulic servo valve, having a first stage which works as a pilot stage, and a second stage which works as a power stage, wherein the second stage has a valve block and a control slide valve sleeve arranged therein and having a jacket surface (18), wherein the jacket surface and/or another region of the control slide valve sleeve is preferably provided with at least one flow passage for transferring control flow and/or volume flow, and wherein a control slide valve is movably arranged in the control slide valve sleeve, wherein at least one of the flow passages is formed by a groove which is arranged in the surface of the control slide valve sleeve and which does not extend sectionally or overall in the peripheral direction of the control slide valve sleeve.
摘要翻译： 本发明涉及一种伺服阀，特别是具有作为先导级的第一级的两级或多级电动液压伺服阀，以及作为动力级工作的第二级，其中第二级具有阀块 以及布置在其中并具有护套表面（18）的控制滑阀套管，其中所述护套表面和/或所述控制滑阀套筒的另一区域优选地设置有至少一个流动通道，用于传递控制流量和/或体积流量 ，并且其中控制滑阀可移动地布置在所述控制滑阀套筒中，其中所述流动通道中的至少一个由布置在所述控制滑阀套筒的表面中并且不在横截面或整体上延伸的凹槽形成 在控制滑阀套筒的周向上。
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公开(公告)号：US11603079B2
公开(公告)日：2023-03-14
申请号：US16770233
申请日：2018-12-07
发明人： Anton Gaile
摘要： The invention relates to a mechanical non-return mechanism for an aircraft application, wherein the aircraft application can be part of a flight control. The non-return mechanism comprises at least one drag brake, at least one main brake, and at least one ball ramp mechanism.
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公开(公告)号：US09702478B2
公开(公告)日：2017-07-11
申请号：US13766080
申请日：2013-02-13
发明人： Joern Frick , Anton Gaile , Franz Weixler
IPC分类号： F16K11/07 , F16K31/42 , F15B13/04 , F15B13/043
CPC分类号： F16K31/42 , F15B13/0402 , F15B13/0433
摘要： The invention relates to a servo valve, in particular a two-stage or multistage electrohydraulic servo valve, having a first stage which works as a pilot stage, and a second stage which works as a power stage, wherein the second stage has a valve block and a control slide valve sleeve arranged therein and having a jacket surface (18), wherein the jacket surface and/or another region of the control slide valve sleeve is preferably provided with at least one flow passage for transferring control flow and/or volume flow, and wherein a control slide valve is movably arranged in the control slide valve sleeve, wherein at least one of the flow passages is formed by a groove which is arranged in the surface of the control slide valve sleeve and which does not extend sectionally or overall in the peripheral direction of the control slide valve sleeve.
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公开(公告)号：US09574578B2
公开(公告)日：2017-02-21
申请号：US14031466
申请日：2013-09-19
发明人： Joern Frick , Anton Gaile , Franz Weixler
CPC分类号： F15B9/17 , B33Y80/00 , B64C13/40 , F15B15/149 , F15B15/202 , F15B2215/30 , Y10T29/49405
摘要： The invention relates to a flap actuator, in particular to a servo/spoiler actuator, comprising at least one electrohydraulic servo valve and at least one actuator which are hydraulically connected to one another, wherein the actuator comprises at least one actuator housing in and/or at which the at least one channel is arranged by means of which one or more components, preferably likewise arranged in and/or at the actuator housing, are hydraulically connected and wherein no valve block is arranged between the actuator and the servo valve.
摘要翻译： 本发明涉及一种翼片致动器，特别涉及一种伺服/扰流器致动器，包括至少一个电动液压伺服阀和至少一个液压连接的致动器，其中致动器包括至少一个致动器壳体和/或 所述至少一个通道布置在所述至少一个通道上，通过所述至少一个通道优选地同样设置在所述致动器壳体中和/或所述致动器壳体中的一个或多个部件被液压连接，并且其中在所述致动器和所述伺服阀之间没有设置阀块。
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