-
-
公开(公告)号：EP4098558A1
公开(公告)日：2022-12-07
申请号：EP21215654.1
申请日：2021-12-17
IPC分类号： B64C1/32 , B64C25/58 , B64D17/80 , B64D25/00 , B64D45/04 , B64C1/14 , B64C7/00 , B64C25/00 , B64C25/30 , B64C25/52 , B64C27/00 , B64D45/06
摘要： The present disclosure provides an aircraft safety lifesaving system, which solves the technical problem that the aircraft lacks a device capable of assisting the aircraft to decelerate and land and buffering the descending impact force, and it is difficult to better ensure the safety of the aircraft and its staff. The lifesaving system comprises an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism is provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body. According to the present disclosure, a safety cabin is provided at the top of the aircraft body, and a deceleration device in the safety cabin is ejected in an emergency to assist the aircraft body to decelerate; the damping and buffering mechanism extends below the wheel body, and the damping and buffering mechanism contacts with the ground first, so that the impact force when the aircraft body descends can be buffered, and serious accidents caused by the impact force when the aircraft body descends can be prevented.
-
公开(公告)号：EP4090591A1
公开(公告)日：2022-11-23
申请号：EP21702844.8
申请日：2021-01-06
发明人： FERREIRA, Sergio , MORAN, Brendan
-
公开(公告)号：EP3750804B1
公开(公告)日：2022-10-19
申请号：EP20179504.4
申请日：2020-06-11
发明人： DURAND, Eric , BEECHER, Scott
-
-
公开(公告)号：EP4063264A1
公开(公告)日：2022-09-28
申请号：EP22174382.6
申请日：2020-06-05
申请人： Schaublin SA
发明人： Coombe, David , Merg, Maxime
摘要： A bushing for aircraft landing gear includes a cylindrical wall having an interior surface defining a bore extending between a first and second axial end thereof and a cylindrical recess extending into the interior surface. The bushing includes a cylindrical self-lubricating liner which is substantially flush with the interior surface is disposed in the recess. The cylindrical wall includes a flange that has an annular recess that receives an annular self-lubricating liner that has a planar axial bearing surface. The planar axial bearing surface is coplanar with an inboard axial surface of the flange. The bushing has an electrically conductive path that conducts electrical current and that extends around the cylindrical self-lubricating liner and the annular self-lubricating liner and through the cylindrical wall and the flange.
-
公开(公告)号：EP4059847A1
公开(公告)日：2022-09-21
申请号：EP22155935.4
申请日：2022-02-09
摘要： According to one embodiment, an aviation system 100 includes electric field sensors 112 and a ground system 114 including a computer configured to communicate with each of the electric field sensors 112. The computer is configured to: acquire electric field intensities from the electric field sensors 112 respectively, and generate a first electric field distribution on a ground surface 16 based on the electric field intensities; derive a matrix; derive a pseudo inverse matrix of the matrix; derive an electric charge distribution on the horizontal plane by multiplying the pseudo inverse matrix by the first electric field distribution on the ground surface 16; and derive a second electric field distribution on a flight path based on the electric charge distribution. The first electric field distribution on the ground surface 16 is derived by multiplying the matrix by electric charges temporarily set on a horizontal plane at a predetermined altitude.
-
公开(公告)号：EP4057513A1
公开(公告)日：2022-09-14
申请号：EP22171328.2
申请日：2017-03-03
摘要： An aircraft sensor system and method for monitoring a component includes a first sensing element of a first digital sensor (12) configured to collect first sensor data, a second sensing element configured to collect second sensor data, a host computer (18), and a first digital bus (22a). The first digital sensor is an accelerometer that is configured to collect and digitize raw acceleration data of a shaft of a gas turbine engine; the second sensing element is a tachometer that is configured to provide one or more pulses indicative of revolutions of the shaft; the host computer is an aircraft avionics system connected to the first digital bus. The first digital sensor (12) comprises a controller (28) configured to obtain the first sensor data and received sensor data via the first digital bus (22a), the received sensor data corresponds to the second sensor data, the controller is configured to process the first sensor data and the received sensor data to perform a Time Synchronous Average, TSA, thereby separating the vibration signatures of components associated with the shaft from other noise sources not synchronous with the shaft. The controller is configured to use the determined TSA to extract condition indicators representative of health of the monitored component, and the first digital sensor (12) is configured to provide the condition indicator and/or the TSA generate processed data, and the first digital sensor (12) is configured to provide the processed data to the host computer (18) via the first digital bus (22a).
-
公开(公告)号：EP3323722B1
公开(公告)日：2022-09-07
申请号：EP16199663.2
申请日：2016-11-18
-
公开(公告)号：EP3269642B1
公开(公告)日：2022-09-07
申请号：EP17180077.4
申请日：2017-07-06
-
-
-
-
-
-
-
-
-
搜索结果
2982 条记录 (耗时 0.024 秒)
