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51.发明公开METHOD AND SYSTEM FOR DETERMINING FRICTION COEFFICIENT FOR AN AIRCRAFT LANDING EVENT 有权VERFAHREN UND SYSTEM ZUR BESTIMMUNG DES REIBUNGSKOEFFIZIENTENFÜREINE FLUGZEUGLANDUNG
公开(公告)号：EP2686243A2
公开(公告)日：2014-01-22
申请号：EP12716520.7
申请日：2012-03-16
发明人： COLLETT, Laura , SCHMIDT, R., Kyle , SARTOR, Pia
CPC分类号： G06F17/5009 , B64C25/00 , B64D2045/008 , G05B17/02 , G05B23/0243
摘要： Method and system of determining ground-to-tire friction coefficient for an aircraft landing event. The method uses an aircraft computational model to repeatedly model the landing event, varying one or more initial conditions of the aircraft model until a best match between a modelled value and a provided value of aircraft vertical acceleration is determined. The method uses initial conditions associated with the best match of modelled and provided vertical acceleration values and a strain value from a sensor on the aircraft landing gear, with the ground-to-tire friction coefficient is a variable. The method models the landing gear to generate a modelled strain value and compares this with the measured strain value, and repeats the landing gear modelling step with a different value for the ground-to-tire friction coefficient until a best match between the modelled strain value and the measured strain value is determined and outputting the respective friction coefficient value.
摘要翻译： 确定飞机着陆事件的地面与轮胎摩擦系数的方法和系统。 该方法使用飞行器计算模型来重复模拟着陆事件，改变飞行器模型的一个或多个初始条件，直到确定了建模值和所提供的飞机垂直加速度值之间的最佳匹配。 该方法使用与建模和提供的垂直加速度值的最佳匹配以及来自飞机起落架上的传感器的应变值相关联的初始条件，其中地对轮胎摩擦系数是变量。 该方法对起落架进行建模以产生建模应变值，并将其与测量的应变值进行比较，并重复起落架建模步骤，其具有不同的地对轮胎摩擦系数值，直到建模的应变值 测定应变值，并输出各摩擦系数值。
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公开(公告)号：EP2509863B1
公开(公告)日：2013-10-16
申请号：EP10718678.5
申请日：2010-04-30
发明人： SIMONNEAUX, Yann
IPC分类号： B64C25/00
CPC分类号： B64C25/001 , B64C2025/003
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公开(公告)号：EP2643214A1
公开(公告)日：2013-10-02
申请号：EP11785062.8
申请日：2011-11-09
发明人： HODGKINSON, Ben , LACY, Stuart , WEBB, Chris , ANSON, Garry
CPC分类号： B64D45/0005 , B64C25/00 , B64D2045/008
摘要： A mechanical position indicator (9a) for providing a visual indication that a first part of an aircraft landing gear (1) has assumed a predetermined position relative to a second part, the position indicator (9a) being arranged to be coupled to a first one of the first and second parts and in a first state arranged to hold an indicator element (15a) in a deployed position, the position indicator (9a) being arranged such that upon the first part assuming the predetermined position relative to the second part, a second one of the first and second parts changes the position indicator (9a) from the first state to a second state in which the indicator element (15a) is displaced from the deployed position, the position indicator (9a) being arranged to inhibit the indicator element (15a) thereafter returning to the deployed position.
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公开(公告)号：EP2195237B1
公开(公告)日：2013-02-27
申请号：EP08836934.3
申请日：2008-10-13
发明人： BENNETT, Ian
CPC分类号： B64C25/34 , B64C25/58 , B64D2045/008 , F16F9/3264
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公开(公告)号：EP2085309B1
公开(公告)日：2010-09-29
申请号：EP09160692.1
申请日：2006-08-04
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公开(公告)号：EP2190737A1
公开(公告)日：2010-06-02
申请号：EP08806330.0
申请日：2008-09-19
发明人： BENNETT, Ian
CPC分类号： B64C25/00 , B64D2045/008 , B64F5/60 , F16C11/045 , F16C17/24 , F16C2326/43 , G01L5/0071
摘要： An overload detecting assembly comprises a first load bearing member (10) adapted to flex laterally in response to a load to be monitored, a second load bearing member (11) spaced from the first under normal load conditions and which is contacted and loaded by the first load bearing member (10) when it is loaded beyond a load limit. Preferably, the first load bearing member (10) has a yield point below the load limit and takes a permanent set once the yield point has been exceeded. A lateral probe (18) cooperates with the first load bearing member as it moves towards the second load bearing member and in turn deflects an indicator member (20) which takes a permanent set when a yield point is exceeded. Ready inspection of the indicator member then reveals whether or not it has been bent.
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公开(公告)号：EP1786669A1
公开(公告)日：2007-05-23
申请号：EP05761554.4
申请日：2005-07-18
发明人： THULBON, Jonathan
摘要： Aircraft landing gear includes a retractable housing comprising an upper leg (11); a lower leg (15) including a wheel axle (16) slidingly disposed within the upper leg (11) and resiliently biassed to an extended condition; a turning collar (18) rotatably disposed about the housing and having connection means for a drag stay (17); and a steering collar (19) operatively connected to a steering motor (41) and connected to the lower leg (15) by a torque link (21, 22); in which the turning collar (18) is provided with a cam surface (24) which cooperates in use with the torque link (21, 22) to maintain the lower leg (15) with the wheel in the fore-and-aft position when in the extended condition.
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公开(公告)号：EP3058110A1
公开(公告)日：2016-08-24
申请号：EP14787048.9
申请日：2014-10-17
摘要： A quenching agent delivery apparatus is provided for delivering a quenching agent to a component to be quenched. The delivery apparatus comprises an inlet through which the quenching agent is configured to be delivered into the apparatus, a first outlet configured to deliver quenching agent in a first direction to an inner surface of the component, and a second outlet configured to deliver quenching agent in a second direction to an inner surface of the component.
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公开(公告)号：EP2350590B1
公开(公告)日：2016-07-20
申请号：EP09796036.3
申请日：2009-11-16
发明人： BENNETT, Ian
CPC分类号： G01L1/06 , B64C25/00 , B64D2045/008
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公开(公告)号：EP3040574A1
公开(公告)日：2016-07-06
申请号：EP15150108.7
申请日：2015-01-05
发明人： HILLIARD, Matthew
CPC分类号： B64C25/64 , B64C25/001 , B64C25/10 , F16F1/128 , F16F7/10 , F16F2222/08
摘要： An aircraft spring assembly (10) includes a helical spring (12) having a hollow core (12c). A polymer damping member (16) is confined within the core (12c) and is narrower than the internal spring diameter so as to be free to move along the core (12c).
摘要翻译： 飞机弹簧组件（10）包括具有中空芯（12c）的螺旋弹簧（12）。 聚合物阻尼构件（16）被限制在芯部（12c）内并且比内部弹簧直径窄，以便沿芯部（12c）自由移动。
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