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1.发明公开AIRCRAFT LANDING GEAR ASSEMBLY INCLUDING A HEALTH AND USAGE MONITORING SYSTEM (HUMS) AND METHOD 审中-公开包括健康和使用监控系统（HUMS）的飞机起落架总成和方法
公开(公告)号：EP3159260A1
公开(公告)日：2017-04-26
申请号：EP15191342.3
申请日：2015-10-23
发明人： Cokonaj, Valerijan
摘要： A health and monitoring system or "HUMS" (20a, 20b) mounted within a hollow structural subassembly (12) of an aircraft landing gear assembly (10), the subassembly having an access port (16) for access to the HUMS without requiring disassembly of the structural subassembly so as to require jacking up the aircraft.
摘要翻译： 安装在飞机起落架组件（10）的中空结构子组件（12）内的健康和监测系统或“HUMS”（20a，20b），所述子组件具有进入HUMS的入口（16），而不需要拆卸 的结构组件，以便要求顶起飞机。
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2.发明授权
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公开(公告)号：EP3336485B1
公开(公告)日：2020-09-23
申请号：EP16204453.1
申请日：2016-12-15
发明人： Cokonaj, Valerijan , Collett, Laura
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公开(公告)号：EP3336485A1
公开(公告)日：2018-06-20
申请号：EP16204453.1
申请日：2016-12-15
发明人： Cokonaj, Valerijan , Collett, Laura
摘要： An aircraft assembly (10) comprising: a first region (14a, CR); a second region (CR, MR) spaced from the first region by a flexible region (12, 18), the first region having greater positional stability than the second region such that flexing of the flexible region due to in-use loads causes the second region to deflect further from its default position than the first region deflects from its default position; and a deflection sensor comprising: a first gyroscope (G1, G2) rigidly mounted at, or with respect to, the first region so as to generate a first signal which represents rotation of the first region about one or more orthogonal axes (α, β, γ); a second gyroscope (G2 - G4) rigidly mounted at, or with respect to, the second region so as to generate a second signal which represents rotation of the second region about one or more orthogonal axes (α, β, γ) the second gyroscope being synchronised in time with the first; and a controller (C) communicatively coupled to the first and second gyroscopes to receive the first and second signals, the controller being configured to subtract one of the first and second signals from the other to obtain a differential signal which represents deflection of second region relative to the first region due to flexing of the flexible region.
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公开(公告)号：EP3159851A1
公开(公告)日：2017-04-26
申请号：EP15191345.6
申请日：2015-10-23
发明人： Cokonaj, Valerijan
CPC分类号： G01N29/04 , B64D2045/008 , G01N29/44 , G01N2291/2694 , G07C5/0808 , G07C5/0841
摘要： An aircraft health and usage monitoring system (HUMS) (10) comprising one or more monitoring sensors (30) arranged to be coupled to an aircraft subassembly (102, 104, 106, 108) to monitor the health of one or more parts of the subassembly and a trigger subsystem. The trigger subsystem comprises a sound transducer (20) and a processor (101), the processor being coupled to the sound transducer to receive and process sound signals from the sound transducer to extract sound information and being coupled to the monitoring sensors to provide control commands to the monitoring sensors. The processor is configured to provide a first control command to the monitoring sensors in response to a first criteria having been met, the first criteria comprising registering first sound information.
摘要翻译： 一种飞机健康和使用监测系统（HUMS）（10），包括一个或多个监测传感器（30），其被布置成联接到飞行器子组件（102,104,106,108），以监测所述飞行器子组件的一个或多个部分的健康状况 子组件和触发子系统。 触发子系统包括声音传感器（20）和处理器（101），处理器耦合到声音换能器以接收和处理来自声音换能器的声音信号以提取声音信息并耦合到监视传感器以提供控制命令 到监控传感器。 处理器被配置为响应于已经满足的第一标准向监视传感器提供第一控制命令，第一标准包括登记第一声音信息。
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