CN103118943A - 结构性部件的加衬板、具有这种加衬板的流动体和监控这种加衬板上的材料损坏的设备 - Google Patents
结构性部件的加衬板、具有这种加衬板的流动体和监控这种加衬板上的材料损坏的设备 Download PDFInfo
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Abstract
本发明涉及一种结构性部件(1)的加衬板(B),其在其以平面方式延伸的内部区域(BI)内以夹层部件的形式实现,所述加衬板包括第一蒙皮部(11)、第二蒙皮部(12)和位于这两个蒙皮部之间的芯部(13),其中所述芯部(13)将所述第一蒙皮部和第二蒙皮部(11,12)以平面方式彼此连接,本发明的特征在于提供延伸经过要监控的芯部(13)的平面区以检测所述芯部(13)内的损坏的多根监控线(14),并且包括分别在第一端(14a)上的第一连接点(15)和在第二端(16a)上的第二连接点(16),目的是施加监控信号(UK),其中所述监控线(14)的撕裂强度是在所述芯部(13)的撕裂强度的50%和100%之间的范围内。
Description
本专利申请要求德国专利申请DE102010027696.0、DE102010027695.2、DE102010031688.1和DE102010031690.3以及美国临时专利申请61/365,857、61/365,882、61/365,873和61/365,863的申请日,它们都是于2010年7月20日提交的。因为上述的引用,这些专利申请披露的内容被包括在本专利申请中。
技术领域
本发明涉及一种结构性部件的加衬板,在其以平面方式延伸的内部区域内以夹层部件的形式实现,所述加衬板包括第一蒙皮部、第二蒙皮部和位于这两个蒙皮部之间的芯部,其中所述芯部将所述第一蒙皮部和第二蒙皮部彼此以平面方式连接,本发明还涉及一种具有这样一种加衬板的流动体和监控加衬板上的材料损坏的设备。
背景技术
这种类型的加衬板是现有技术中是已知的,在各种行业用作表面设计的覆盖部件。因为其结构简单,这些部件使得实现各种不同表面形状成为可能,使得这类部件比如适合用作车辆内装饰。但是,这种夹层部件的缺点是其比较软的芯部在机械负荷下、尤其是撞击负荷下容易撕裂。因为所述芯部是用蒙皮部在两边覆盖着,在不对所述部件进行破坏性试验的情况下,难以确定所述部件是否受到了破坏。
尤其是在载人航空领域,飞机的可操作性以及安装于其中的部件的结构完整性扮演着重要的角色。与安全相关的部件的不可检测的致命破坏会导致各种机械系统故障,因此具有灾难性后果。在飞机行业,因而要检查、修理与安全相关的部件,如果所述破坏不再能在预定的时间内(即根据维修时间表)进行经济地修理,有可能替换掉所述部件。在飞行操作中,飞机的加衬板不断受到其它物体的可能的撞击。飞机经常被石块、雷雨中的冰雹或者甚至是进入飞机的飞行路径的鸟类砸中。这种异物体或者其一部分对以夹层结构形式实现的铺板部件的撞击必须分类,是尤其关键的,因为所述夹层结构受到的变形会造成其内部的泡沫核心撕裂或者与周围的蒙皮部分开,而这种破坏从外部看不到。
这就是这种夹层部件迄今为止还未被用作飞机构造、尤其是商用飞机中的加衬板的与安全相关的部件的原因。
发明内容
本发明的目的是披露一种具有可能最低重量的结构性部件的加衬板、具有这种加衬板的流动体以及用于监控加衬板上的材料损坏的设备,该加衬板可以用于安全至关重要的部件结构的主负荷承受区域。
这个目的是用独立权利要求的特征来达到的。其它实施例是在引用这些独立权利要求的从属权利要求中描述。
所述创新性解决方案允许进行加衬板的非破坏性试验(非破坏性试验),尤其是所有类型破坏的可靠检测。
根据本发明的加衬板方案,提出形成以泡沫材料的夹层结构形式实现的加衬板的芯部,以及在所述飞机结构的主负荷承受区域内利用这个加衬板,而不用管它的易受损害性。但是,所述芯部的材料的完整性(结构完整性)是通过撕裂强度量低于所述芯部的平面区域的断裂强度的至少一根监控线来检查的,使得所述芯部中的破坏可以以非破坏性的、简单的、可靠的方式来检测。通过这种方式,所述加衬板可以用作耐破坏的加衬板,使得它尤其适于用作飞机结构的一部分。
“主负荷承受区域”一词指的是飞机结构的一个区域,在飞行中,如果所述破坏的发生使得这个区域不再能够承受由施加在飞机结构上的主负荷所产生的张力的话,该区域的破坏会导致飞机的灾难性事件。
本发明提出一种结构性部件的加衬板,其在其以平面方式延伸的内部区域内以夹层部件的形式实现,所述加衬板的特征是有第一蒙皮部、第二蒙皮部和位于这两个蒙皮部之间并且将所述第一蒙皮部和第二蒙皮部彼此以平面方式连接的芯部。为了检测就损坏的出现受到监控的芯部的虚构的监控块中的损坏,在这个监控块中设置至少一根监控线或者设置延伸经过要被监控的所述芯部的监控块的多根监控线。根据各个应用,所述一根或多根监控线以一种方式设置在所述监控块内,使得所述监控块的损坏监控得以实现。每根监控线可以分别有在第一端的第一连接点、在第二端的第二连接点以施加监控信号。代替的,一个连接点可以联接在几根监控线上。在这种情况下,所述监控线的撕裂强度尤其在所述芯部的撕裂强度的50%和100%之间的范围内。
这样一种布局提供的优点是,在所述加衬板的芯部出现缺陷之后,可以立即检测到它们,这样可以非常快速地识别出有缺陷的部件,以将其随后替换掉。
在本发明的另一个实施例中,所述监控线的撕裂强度在所述芯部的撕裂强度的80%和100%之间的范围内,但是尤其优选的是所述监控线的撕裂强度在所述芯部的撕裂强度的90%和100%之间或者90%和95%之间。
而且,所述芯部可以有一个1.5MPa和2.5MPa之间范围内的张力强度和/或0.8MPa和1.6MPa之间范围内的剪切强度。
根据本发明的一个实施例,提出所述监控块内的至少一根监控线在所述加衬板内以曲折形状的方式延伸,以便形成沿着所述加衬板的厚度方向延伸、在相对设置的蒙皮部之间的桥接段以及分别连接这些桥接段并分别位于其中一个相对设置的蒙皮部中的回行段(reversing segments),其中在所述监控线纵向上的一个在另一个后面的回行段位于不同的蒙皮部内。在这种情况下,所述至少一根监控线的连接点可以位于不同的蒙皮部,或者在同一个蒙皮部内。
此外,多根监控线可以在所述加衬板的厚度方向上延伸,其中每根监控线的特征是有两个连接点,并且其中第一连接点位于所述第一蒙皮部,第二连接点位于所述第二蒙皮部。
因为有这个布局,可以以特别简单的方式检测到延伸横跨所述厚度方向的芯部的撕裂的形成。
根据本发明的实施例,每根监控线的特征是有两个连接点。根据另一个实施例,至少一个连接点被提供在和联接在几根监控线上。
在本发明的另一个实施例中,多根监控线可以在所述加衬板的纵向上延伸,其中每根监控线的特征是有两个连接点,这两个连接点都位于所述第一蒙皮部或者它们都位于所述第二蒙皮部上。
因为有这个布局,可以用特别简单的方式检测到沿着所述加衬板的厚度方向延伸并且因此横跨其纵向的芯部内的撕裂的形成。
另外,所述监控线可以由导电体构成,所述连接点可以由电连接点构成,所述监控信号可以是监控电压信号。
这提供的优点是,所述监控电压可以分别施加在一个导电体上。如果电流没有出现在所述导电体内,或者偏离了预定的电流值,可以确定所述导电体以及还有所述芯部受到了破坏。
所述监控线可以另外由光波导构成,所述连接点可以由光连接点构成,所述监控信号可以是光监控信号。
利用所述光波导作为监控线提供的优点是,与导电体相比,不会有例如产生自磁场的干扰信号被感应到,使得损坏检测也可以在磁场内可靠地进行。当飞机飞过出现产生磁场的雷击的雷雨时,这尤其有利。
此外,所述监控信号可以持续地施加在所述监控线上,或者所述监控信号可以在预定的时间期间在预定的时间间隔内施加到所述监控线。
所述第一种变型提供的优点是可以立即检测到损坏。如果持续施加监控信号,线路中断导致立即有信号损失,因此导致中间缺陷检测。所述第二种替换例提供的优点是,维修人员有一贯的检查行为,使得其维修活动可以更精确地定义和优化。而且,在大多数情况下,静止状态下的测量比工作状态下的测量更为可靠。
根据一个本发明实施例,所述加衬板的芯部是由同质材料形成。
而且所述芯部可以由泡沫芯尤其是泡沫铝芯、陶瓷芯或者夹层芯构成或者形成。根据另一个实施例,所述芯部本身的特征是有一个中间层和/或是以由几个夹层芯合成的复合芯的形式实现的。
此外,所述监控线的撕裂强度可以与1.5MPa和2.5MPa之间范围内的张力强度以及0.8MPa和1.6MPa之间的剪切强度相对应。
本发明的另一个方面涉及一种带有加衬板的流动体,尤其是用于飞机。
根据另一个示例性实施例,提出了一种监控加衬板上的材料或者结构损坏的设备,其中所述监控设备包括经由所述监控线传输信号的启动设备,以及评估设备,通过所述评估设备,基于经由所述监控线传输的所述信号可以判断所述监控线是否未受损,目的是检测所述泡沫区中的损坏,其中以一种方式设计所述启动设备,使得它经由所述监控线持久地或者在预定的时间间隔内传输所述监控信号。
附图说明
下面参考所附示意图描述本发明的示例实施例,其中:
图1所示为具有本发明加衬板的一段飞机尾翼单元的俯视图,
图2所示为根据本发明第一实施例贯穿加衬板的局部截面,其中加衬板包括沿芯部的纵向上延伸的监控线,目的是检测芯部的监控块的损坏,
图3所示为根据本发明另一个实施例的贯穿加衬板的局部截面,其中加衬板包括在核心层内以曲折形状的方式延伸的监控线,其中联接在这个监控线上的连接设备分别被设置在不同的蒙皮部,
图4所示为根据本发明另一个实施例的贯穿加衬板的局部截面,其中加衬板包括在核心层内以曲折形状的方式延伸的监控线,其中联接在这个监控线上的连接设备分别被设置在同一个蒙皮部,
图5所示为穿过具有所述监控线的布局的几种变型的加衬板的局部截面,
图6所示为贯穿根据第二实施例的加衬板的局部截面,
图7所示为贯穿加衬板的另一个局部截面。
具体实施方式
图1展示的是具有多个加衬板(planking panel)B的结构性部件1,所述加衬板B至少局部形成结构性部件1的表面。结构性部件1可以包括流动体1,比如例如飞机的尾翼单元、尤其是飞机的机翼、升降舵、方向舵或者机身的一部分。
图示了一个用于定位目的的坐标系统,该坐标系统分别定义了飞机机翼或者结构性部件以及加衬板B的弦向T、翼展方向S和厚度方向D。
图2同样也图示了这个坐标系统,图2所示的是异物体F与加衬板元件B的碰撞。图2所示的是沿着在图1中的厚度方向D和翼展方向S所界定的平面内延伸的截面线的局部截面。加衬板部件B包括参考厚度方向D在其上方区域的第一蒙皮部11,参考厚度方向D在其相对设置的下方区域的第二蒙皮部12。蒙皮部11、12,与它们的横向尺寸相比,厚度较小,因此形成平面的、板状体。提供在第一蒙皮部11和第二蒙皮部12之间的核心层13的厚度大于蒙皮部11、12的厚度。在其上表面,核心层13与第一蒙皮层11平面接触。并且,核心层13还与第二蒙皮层12在其下表面平面接触。平面接触可以被另外加强,比如通过在所述核心层和蒙皮层之间提供粘结剂或者通过进行螺接或者铆接。根据图1,加衬板B的特征是有内部区域IB,监控线14在该内部区域IB内延伸。
在图2图示的本发明第一实施例中,监控线14在加衬板B的纵向上延伸穿过加衬板B的核心层13。监控线14具有第一端14a和第二端14b,其中第一端14a连接在第一连接点15,第二端16a连接在第二连接点16。连接点15、16两者都设置在第一蒙皮层11中,但是在本发明替代实施例中,也可以被设置在第二蒙皮层12中。监控信号可以经由连接点15、16从外部施加在监控线14上,其中所述监控信号是从第一连接点15传送到第二连接点16,或者相反。
所用的监控线14可以由导电体或者光波导构成,比如,光缆。然后,对应这些监控线的监控信号需要以电信号或者光信号的形式施加的。设置在加衬板B中的外部诊断系统或者内部诊断系统判断所施加的信号是否经由监控线14传输。利用导电体可以制造特别节约成本的加衬板部件B,其中导电体的高鲁棒性减少了加衬板B制造过程中所需的工作。利用光监控线的优点是,加衬板B不易受到电磁干扰的影响。
图7所示为本发明的第一实施例,其中这个图示出了作为根据图2的异物体F的撞击结果所形成的示例裂缝R。这个撞击导致整个加衬板B偏斜,其中面板内部的芯部13受到在其纵向上作用的张应力。如果这个张应力超过了最大材料值,以至于形成所示的裂缝,芯部13裂开。监控线14沿着加衬板B的纵向延伸,其撕裂强度与芯部13的材料的撕裂强度基本上一致。这意味着芯部13的撕裂直接导致监控线14的截断。因此不能进行信号传输,诊断设备检测到缺陷。在图7中,监控电压Uk在连接点15、16处施加给监控线14,使得预定的电流强度形式的监控信号流经监控线14。
但是,为了检测损坏,信号传输不必完全失效。在本发明的可替换实施例中,可以施加电压UK形式的监控信号,电压UK在监控线14内产生具有预定电流值的电流流动。如果诊断设备测量到具有预定电流值的电流,则确定不存在损坏。但是,如果检测到电流值偏离了预定的电流值,则判断加衬板B受到了损坏。这个实施例本质上可以与只有电流值“零”定义损坏情景的实施例结合。
监控信号可以持久地或者以脉冲的方式流经监控线14。当监控线14中断时,从其中断时刻开始,不再出现信号传输,其中这由同时也输出监控信号的诊断设备立即检测到。在脉冲信号应用中,诊断设备通过在损坏情景之后施加给监控线14的、不能被传输的第一信号判断在加衬板B上存在着损坏。用这种方式,与持久的信号传输相比,可以节省能量。
监控线14具有与芯部13的材料属性相适配的撕裂强度。在这个方面,其撕裂强度在芯部13的材料的撕裂强度的50%和100%之间、优选的是在80%和100%之间、尤其是在90%和100%之间的范围内。这使之可以确保当芯部13受到撕裂形式的损坏时,监控线14也被损坏。在本发明的另一个优选实施例中,监控线14的撕裂强度在芯部13的材料的撕裂强度的80%和95%之间的范围内。这个实施例提供的优点是,即使芯部13还没有受到损坏、而是仅受到其材料的边缘负荷范围内的负荷时,监控线14也会在对应区域被割断,其中诊断系统必然检测到加衬板B至少受到边缘范围内的负荷。随后,诊断设备可以预先输出警告消息,使得在发生实际损坏情景之前可以替换掉加衬板B。
监控线14的撕裂强度优选的是对应于1.5MPa和2.5MPa之间的张力强度,但是优选的是、尤其是等于1.9MPa,和/或在0.8MPa和1.6MPa之间的剪切强度,但是优选的是等于1.15MPa。
图5所示为监控线14的布局的几种变化,其中监控线14的连接点15、16不必必须被提供在同一个蒙皮部上。监控线14可以基本上与厚度方向D平行地从第一蒙皮部11延伸到第二蒙皮部12。蒙皮部11、12可以可替换地或者另外垂直设置,使得监控线14基本上平行于弦向T延伸。而且图5示出了一个示例的裂缝R,想象它可以是在图1所示的异物体F撞击之后形成。所述裂缝与至少一根监控线14交叉,使得沿着这些割断的监控线14不再可能进行信号传输。
图6展示的是本发明的另一个实施例,其中夹层部件形式的加衬板B的结构与参考图1所描述的结构一致。但是,在这种情况下,监控线14从第一蒙皮部11延伸到第二蒙皮部12,被提供在加衬板B的预定关键点K。所示的裂缝基本上与蒙皮部11、12平行地延伸,因此横断监控线14。横向撞击在加衬板B边上的异物体F产生用向量FK形式图示的冲力,导致加衬板B压缩。所述有效力量使蒙皮部11、12偏转,即,偏离芯部域13,以至于形成所示的裂缝R。在这种情况下,裂缝R还割断监控线14,使得不能再传输监控信号,诊断设备判断加衬板已经被损坏。
根据本发明提供在监控块KV内的监控线或者监控线布局可以在监控块VK内有区别地延伸。图3展示了本发明的一个优选实施例,其中加衬板B的特征是有一个在核心层或者芯部13内以曲折形状的方式延伸的监控线14,其中联接在这个监控线14上的连接设备15、16分别被提供在不同的蒙皮部11和12上。图4展示的是这个实施例的变型,其中加衬板B的特征是有一个在核心层或者芯部13内以曲折形状的方式延伸的监控线14,其中联接在这根监控线14上的连接设备15、16分别被提供在同一个蒙皮部11或12上。
Claims (15)
1.一种结构性部件(1)的加衬板(B),在其以平面方式延伸的内部区域(BI)内以夹层部件的形式实现,所述加衬板包括第一蒙皮部(11)、第二蒙皮部(12)和位于这两个蒙皮部之间并将所述第一蒙皮部和第二蒙皮部(11,12)以平面方式彼此连接的芯部(13),其中,
所述加衬板(B)包括为了施加监控信号而分别联接到第一连接点(15)和第二连接点(16)、为了检测芯部(13)的监控块(KV)的损坏而延伸过芯部(13)区域的至少一根监控线(14),其中监控线(14)具有一个撕裂强度,其量是在芯部(13)的平面区域的断裂强度的量的50%和100%之间的范围内。
2.根据权利要求1的加衬板(B),其中,芯部(13)具有在1.5MPa和2.5MPa之间范围内的张力强度和/或在0.8MPa和1.6MPa之间范围内的剪切强度。
3.根据权利要求1的加衬板(B),其中,至少一根监控线(14)在加衬板(B)内以曲折形状的方式延伸,以便形成沿着加衬板(B)的厚度方向延伸、在相对设置的蒙皮部(11,12)之间的桥接段(14a)以及分别连接这些桥接段并分别位于其中一个相对设置的蒙皮部(11,12)中的回行段(14b)。
4.根据权利要求3的加衬板(B),其中,至少一个监控线(14)的连接点(15,16)位于不同的蒙皮部(11,12)内。
5.根据权利要求3的加衬板(B),其中,至少一个监控线(14)的连接点(15,16)位于蒙皮部(11,12)的同一个蒙皮部内。
6.根据权利要求1的加衬板(B),其中,所述加衬板(B)包括沿着加衬板(B)的厚度方向(D)延伸的多根监控线(14),其中每根监控线(14)具有两个连接点(15,16),其中第一连接点分别位于第一蒙皮部(11)上,第二连接点分别位于第二蒙皮部(12)上。
7.根据权利要求1的加衬板(B),其中,所述加衬板(B)包括沿着加衬板(B)的纵向延伸的多根监控线(14),每根监控线(14)具有两个连接点(15,16),这两个连接点(15,16)都位于第一蒙皮部(11)上,或者都位于第二蒙皮部(12)上。
8.根据权利要求1的加衬板(B),其中,监控线(14)包括导电体,所述连接点(15,16)包括电连接点,所述监控信号包括监控电压。
9.根据权利要求1的加衬板(B),其中,所述监控线(14)包括光波导,所述连接点(15,16)包括光连接点,所述监控信号包括光监控信号。
10.根据权利要求1的加衬板(B),其中,所述芯部(13)由优选地是比两个蒙皮部(11,12)轻的同质材料构成。
11.根据权利要求1的加衬板(B),其中,所述芯部(13)由泡沫芯构成,尤其是由聚合物泡沫芯、泡沫铝芯、陶瓷芯或者实心构成。
12.根据权利要求1的加衬板(B),其中,所述芯部(13)由几个夹层芯组成的复合芯构成。
13.根据权利要求1的加衬板(B),其中,所述监控线(14)的撕裂强度对应于1.5MPa和2.5MPa之间范围内的张力强度和0.8MPa和1.6MPa之间的剪切强度。
14.一种流动体,尤其是飞机的流动体,其具有根据权利要求1的加衬板(B)。
15.一种用于监控根据前述权利要求其中一项权利要求的加衬板(B)的材料损坏的设备,其中,所述监控设备包括用于经由所述监控线(14)传输信号的启动设备以及评估设备,通过所述评估设备,基于经由所述监控线(14)传输的所述信号,能够判断所述监控线是否完好,目的是检测所述泡沫区中的损坏,其中以一种方式设计所述启动设备,使得它经由所述监控线(14)持久地或者在预定的时间段内传输所述监控信号(UK)。
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US36587310P | 2010-07-20 | 2010-07-20 | |
DE102010027695A DE102010027695A1 (de) | 2010-07-20 | 2010-07-20 | Strukturbauteil mit zumindest einer hauptlast-tragende Beplankungsschale und einer Trägerstruktur zur Befestigung der hauptlast-tragenden Beplankungsschale sowie Strömungskörper mit einem solchen Strukturbauteil |
DE102010031690A DE102010031690A1 (de) | 2010-07-20 | 2010-07-20 | Beplankungsplatte für ein Strukturbauteil, Strömungskörper mit einer solchen Beplankungsplatte sowie Vorrichtung zur Überwachung eines Materialschadens an einer Beplankungsplatte |
US61/365,857 | 2010-07-20 | ||
DE102010027695.2 | 2010-07-20 | ||
DE102010027696A DE102010027696A1 (de) | 2010-07-20 | 2010-07-20 | Hauptlast-tragende Beplankungsschale sowie Strukturbauteil mit zumindest einer hauptlast-tragenden Beplankungsschale |
DE102010027696.0 | 2010-07-20 | ||
DE102010031688.1 | 2010-07-20 | ||
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DE102010031688A DE102010031688A1 (de) | 2010-07-20 | 2010-07-20 | Hauptlast-tragende Beplankungsschale sowie Strukturbauteil und Strömungskörper mit einer solchen hauptlast-tragenden Beplankungsschale |
US61/365,882 | 2010-07-20 | ||
PCT/EP2011/003644 WO2012010307A1 (de) | 2010-07-20 | 2011-07-20 | Beplankungsplatte für ein strukturbauteil, strömungskörper mit einer solchen beplankungsplatte sowie vorrichtung zur überwachung eines materialschadens an einer beplankungsplatte |
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CN2011800453006A Pending CN103118943A (zh) | 2010-07-20 | 2011-07-20 | 结构性部件的加衬板、具有这种加衬板的流动体和监控这种加衬板上的材料损坏的设备 |
CN201180045258.8A Active CN103118939B (zh) | 2010-07-20 | 2011-07-20 | 主负荷承受蒙皮壳和具有主负荷承受蒙皮壳的结构性部件 |
CN201180045269.6A Active CN103153782B (zh) | 2010-07-20 | 2011-07-20 | 主负载蒙皮壳及带有该主负载蒙皮壳的结构件和流动体 |
CN201180045272.8A Active CN103118940B (zh) | 2010-07-20 | 2011-07-20 | 具有至少一个主负荷承载蒙皮外壳和联接该主负荷承载蒙皮外壳的支撑结构的结构件以及具有这种结构件的流动体 |
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CN201180045269.6A Active CN103153782B (zh) | 2010-07-20 | 2011-07-20 | 主负载蒙皮壳及带有该主负载蒙皮壳的结构件和流动体 |
CN201180045272.8A Active CN103118940B (zh) | 2010-07-20 | 2011-07-20 | 具有至少一个主负荷承载蒙皮外壳和联接该主负荷承载蒙皮外壳的支撑结构的结构件以及具有这种结构件的流动体 |
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US (4) | US20130273301A1 (zh) |
EP (4) | EP2603430B1 (zh) |
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US20140000381A1 (en) | 2014-01-02 |
US9296463B2 (en) | 2016-03-29 |
EP2595877A1 (de) | 2013-05-29 |
EP2595878B1 (de) | 2017-05-03 |
EP2595876B1 (de) | 2016-07-06 |
EP2595876A1 (de) | 2013-05-29 |
EP2595877B1 (de) | 2016-05-11 |
US9371128B2 (en) | 2016-06-21 |
US20140050884A1 (en) | 2014-02-20 |
US20130273301A1 (en) | 2013-10-17 |
WO2012010307A1 (de) | 2012-01-26 |
EP2595878A1 (de) | 2013-05-29 |
CN103118940B (zh) | 2017-01-18 |
CN103118939B (zh) | 2016-01-20 |
CN103118939A (zh) | 2013-05-22 |
CN103153782B (zh) | 2017-02-15 |
WO2012010306A1 (de) | 2012-01-26 |
WO2012010304A1 (de) | 2012-01-26 |
WO2012010305A1 (de) | 2012-01-26 |
EP2603430A1 (de) | 2013-06-19 |
US20130266756A1 (en) | 2013-10-10 |
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