CN114348241A - 飞行器的涵道螺旋桨、飞行器及飞行器的构件 - Google Patents
飞行器的涵道螺旋桨、飞行器及飞行器的构件 Download PDFInfo
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Abstract
一种飞行器的涵道螺旋桨(17),具有:转子侧的螺旋桨;定子侧的涵道体(19),其在径向外部包围该螺旋桨并且限定用于流经该螺旋桨(18)的空气的流动通道(22),其中该涵道体(19)具有朝向该螺旋桨的内壁(23),该涵道体(19)具有背离该螺旋桨的外壁(24),在该涵道体(19)的内壁(23)与外壁(24)之间布置有至少两个在该涵道螺旋桨的轴向方向(A)上毗连的蜂窝芯(25,26,27),这些蜂窝芯的蜂窝(36)在该涵道螺旋桨的径向方向(R)上延伸,并且在该涵道螺旋桨的轴向方向(A)上毗连的蜂窝芯中的至少一个蜂窝芯(27)至少在其与相应邻接的蜂窝芯(25,26)的相应的接触面(33,34)的区域中由至少一个纤维增强塑料层缠绕。
Description
技术领域
本发明涉及一种飞行器的涵道螺旋桨(Mantelpropeller)和一种飞行器。本发明还涉及一种飞行器的构件。
背景技术
DE 10 2018 116 144 A1公开了一种具有机身和接合在机身上的机翼的飞行器。涵道螺旋桨整合到机翼中。涵道螺旋桨可以被板条覆盖。涵道螺旋桨可以水平或竖直地固定。水平固定的涵道螺旋桨用于在垂直起飞或垂直降落中驱动飞行器。竖直固定的涵道螺旋桨用于产生飞行器的推力。
从DE 10 2018 123 470 A1中已知一种飞行器,其中将多个涵道螺旋桨整合到一个机翼中。
从DE 10 2018 116 147A1中已知另一种飞行器。在此,螺旋桨接合在飞行器的机身的机鼻上,这些螺旋桨支持飞行器的垂直起飞或垂直降落。
从DE 10 2018 116 153 A1中已知一种飞行器,其中涵道螺旋桨接合在飞行器的机身、即机身的机鼻上。在此,将两个涵道螺旋桨组合成一个单元,该单元可以围绕旋转轴线枢转,其中这个旋转轴线与飞行器的俯仰轴线平行地延伸。
DE 10 2018 116 166 A1公开了飞行器的涵道螺旋桨的原理结构。涵道螺旋桨包括转子侧的螺旋桨(其也被称为转子)以及定子侧的涵道体,其中涵道体在径向外部包围该螺旋桨。涵道体限定在轴向方向上延伸的、用于流经螺旋桨的空气的流动通道。
从DE 10 2018 116 149 A1中已知另一种飞行器涵道螺旋桨。
DE 10 2018 120 200 A1同样公开了一种飞行器涵道螺旋桨。在这种涵道螺旋桨中,电动机器整合到涵道体中。
飞行器的涵道螺旋桨应尽可能轻地构造。此外,飞行器的涵道螺旋桨必须具有足够的稳定性和刚性。迄今为止,完全满足这两个前提条件是困难的。
从DE 10 2008 060 550 B3中已知一种飞行器的底板,该底板具有蜂窝结构和用于蜂窝结构的两个外部盖层。蜂窝结构和这两个盖层形成夹心构件。蜂窝结构由塑料构成。盖层由纤维增强塑料构成。
发明内容
本发明的目的在于,提供一种新型的飞行器涵道螺旋桨、一种具有这种涵道螺旋桨的飞行器和一种飞行器的构件。
这个目的通过下文所述的涵道螺旋桨来实现。
该涵道螺旋桨具有转子侧的螺旋桨和定子侧的涵道体(Mantel),该涵道体在径向外部包围该螺旋桨并且限定用于流经该螺旋桨的空气的流动通道。
该涵道体具有朝向该螺旋桨的内壁,该内壁由至少一个纤维增强塑料层制成。该涵道体还具有背离该螺旋桨的外壁,该外壁由至少一个纤维增强塑料层制成。
在该涵道体的内壁与外壁之间布置有至少两个在该涵道螺旋桨的轴向方向上毗连的蜂窝芯,这些蜂窝芯的蜂窝在该涵道螺旋桨的径向方向或大致在径向方向上延伸。
在该涵道螺旋桨的轴向方向上毗连的蜂窝芯中的至少一个蜂窝芯至少在其与相应邻接的蜂窝芯的相应的接触面的区域中由至少一个纤维增强塑料层缠绕或包裹。
根据本发明的涵道螺旋桨在结构上是简单的并且具有较高的稳定性和刚性。这由以下方式保证,一方面:在该涵道螺旋桨的涵道体的内壁与外壁之间布置有至少两个蜂窝芯,这些蜂窝芯的蜂窝在该涵道螺旋桨的径向方向上延伸;另一方面:在该涵道螺旋桨的轴向方向上毗连的蜂窝芯中的至少一个蜂窝芯至少在其相应的接触面的区域中由该至少一个纤维增强塑料层缠绕或包裹。
这保证了涵道体的内壁与外壁之间的良好的力传递。
毗连的蜂窝芯之一由于力作用而塌陷或溃缩的危险是不存在的。
优选地,在该涵道螺旋桨的轴向方向上毗连的蜂窝芯中的至少一个蜂窝芯完全由该至少一个纤维增强塑料层缠绕或包裹。这对于确保简单的制造过程以及从内壁朝向外壁方向的力传递是特别优选的。
优选地,在每两个在涵道螺旋桨的轴向方向上毗连的蜂窝芯中,该每两个蜂窝芯中的仅一个蜂窝芯至少在其接触面的区域中由该至少一个纤维增强塑料层缠绕或包裹。这对于尽可能低地保持制造成本是优选的。
根据一个有利的改进方案,该涵道螺旋桨的涵道体在轴向位置处具有切口,该切口容纳进入体该涵道螺旋桨的螺旋桨的转动叶片在运行中能够进入到该进入体中,其中至少在其相应接触面的区域中由至少一个纤维增强塑料层缠绕或包裹的蜂窝芯延伸过该进入体的整个轴向延伸尺寸。这对于从内壁朝向外壁方向的最佳力传递是特别优选的。尤其在运行中螺旋桨或转子可以进入到进入体的位置处并且在运行中产生较大的力的位置处,这些力可以从内壁朝向外壁的方向传递。
该飞行器在下文中进行限定。
该飞行器的构件、尤其是涵道螺旋桨的涵道体在下文8中进行限定。
总体上,本发明在此公开下述1、6和8的技术方案,下述2-5、7和9-10为优选技术方案:
1.一种飞行器的涵道螺旋桨(17),该涵道螺旋桨具有:
转子侧的螺旋桨(18);
定子侧的涵道体(19),该涵道体在径向外部包围该螺旋桨(18)并且限定用于流经该螺旋桨(18)的空气的流动通道(22),
其中该涵道体(19)具有朝向该螺旋桨(18)的内壁(23),该内壁由至少一个纤维增强塑料层制成,
其中该涵道体(19)具有背离该螺旋桨(18)的外壁(24),该外壁由至少一个纤维增强塑料层制成,
其中在该涵道体(19)的内壁(23)与外壁(24)之间布置有至少两个在该涵道螺旋桨(17)的轴向方向(A)上毗连的蜂窝芯(25,26,27),这些蜂窝芯的蜂窝(36)在该涵道螺旋桨的径向方向(R)或大致在径向方向(R)上延伸,
其中在该涵道螺旋桨(17)的轴向方向(A)上毗连的蜂窝芯中的至少一个蜂窝芯(27)至少在其与相应邻接的蜂窝芯(25,26)的相应的接触面(33,34)的区域中由至少一个纤维增强塑料层缠绕或包裹。
2.根据上述1所述的涵道螺旋桨(17),其特征在于,这些毗连的蜂窝芯中的至少一个蜂窝芯(27)完全由该至少一个纤维增强塑料层缠绕或包裹。
3.根据上述1或2所述的涵道螺旋桨(17),其特征在于,在每两个毗连的蜂窝芯(25,27;26,27)中,该每两个蜂窝芯中的仅一个蜂窝芯(27)至少在其接触面(33,34)的区域中由该至少一个纤维增强塑料层缠绕或包裹。
4.根据上述1至3之一所述的涵道螺旋桨(17),其特征在于,
该涵道体(19)的内壁(23)由第一数量的纤维增强塑料层构成,
该涵道体(19)的外壁(24)由第二数量的纤维增强塑料层构成,该第一数量大于该第二数量。
5.根据上述1至4之一所述的涵道螺旋桨(17),其特征在于,该涵道体(19)在轴向位置处具有切口(32),该切口容纳进入体(32),该螺旋桨(18)的转动叶片在运行中能够进入到该进入体中,其中至少在其接触面(33,34)的区域中由至少一个纤维增强塑料层缠绕或包裹的蜂窝芯(27)延伸过该进入体(32)的整个轴向延伸尺寸。
6.一种飞行器(10),该飞行器具有:
提供乘客舱的机身(11);
接合在该机身(11)上的机翼(13);
至少一个涵道螺旋桨(17),该至少一个涵道螺旋桨接合在该机身(11)或这些机翼(13)上,
其特征在于,
相应的涵道螺旋桨(17)是根据上述1至5之一形成的。
7.根据上述6所述的飞行器,其特征在于,相应的涵道螺旋桨(17)接合在一个机翼(13)上。
8.一种飞行器的构件,尤其涵道螺旋桨(17)的涵道体(19),该涵道体具有:
由至少一个纤维增强塑料层制成的第一壁(23);
由至少一个纤维增强塑料层制成的第二壁(24);
至少两个布置在该第一壁(23)与该第二壁(24)之间的蜂窝芯(25,26,27),这些蜂窝芯的蜂窝(36)在该第一壁(23)与该第二壁(24)之间延伸,并且这些蜂窝相对于这些蜂窝(36)的延伸方向垂直地毗连,
其中这些毗连的蜂窝芯中的至少一个蜂窝芯(27)至少在其与相应邻接的蜂窝芯(25,26)的相应的接触面(33,34)的区域中由至少一个纤维增强塑料层缠绕或包裹。
9.根据上述8所述的构件,其特征在于,这些毗连的蜂窝芯中的至少一个蜂窝芯(27)完全由该至少一个纤维增强塑料层缠绕或包裹。
10.根据上述8或9所述的构件,其特征在于,在每两个毗连的蜂窝芯(25,27;26,27)中,该每两个蜂窝芯中的仅一个蜂窝芯(27)至少在其接触面(33,34)的区域中由该至少一个纤维增强塑料层缠绕或包裹。
附图说明
本发明的优选改进方案自从属权利要求和以下说明中确定。将借助附图详细说明本发明的实施例,但并不局限于这些实施例。在附图中:
图1示出了飞行器的侧视图;
图2示出了飞行器的俯视图;
图3示出了飞行器的涵道螺旋桨与板条单元一起的透视图;
图4示出了涵道螺旋桨的涵道体的透视图;以及
图5示出了图4的截面V-V与放大的细节。
具体实施方式
图1和图2示出了飞行器10的不同视图。飞行器具有机身11,该机身尤其提供乘客舱。此外,飞行器10具有接合在机身11上的机翼13。
飞行器10是所谓的垂直起降飞行器,该垂直起降飞行器在起飞时从地面上垂直上升,并且在降落时垂直降落在地面上。
为了能够实现飞行器10的这种垂直起飞和降落,飞行器10至少在每个机翼13的区域中各自具有至少一个机翼抬升单元14,该机翼抬升单元也被称为机翼升降单元(Wing-Lift-Unit,WLU)。在示出的实施例中,每个机翼13各自具有三个这种机翼抬升单元14。
通过使用机翼抬升单元14进行的飞行器10的垂直起飞和降落可以受到至少一个机鼻抬升单元15的辅助,该机鼻抬升单元接合在飞行器10的机身11的机鼻16上。机鼻抬升单元15也被称为机鼻升降单元(Nose-Lift-Unit,NLU)。在图1和图2中示出了这种机鼻抬升单元15,该机鼻抬升单元定位在机身11的一侧。还可以使用两个这种机鼻抬升单元15。机鼻抬升单元15优选地是可以相对于机身11枢转的,尤其使得在起飞和降落时,相应的机鼻抬升单元15从机身11中枢转出来,而针对飞行器10起飞后并且降落前的飞行运行,相应的机鼻抬升单元15枢转进入机身11。
为了在飞行器10起飞后推进飞行器,飞行器10具有至少一个推进单元12,在示出的实施例中具有两个整合到机身11后部的推进单元12。
飞行器10的相应的机翼抬升单元14和相应的机鼻抬升单元15以及相应的推进单元12可以包括涵道螺旋桨17。
图3示出了机翼抬升单元14的透视图,该机翼抬升单元包括涵道螺旋桨17。涵道螺旋桨17在此具有转子侧的螺旋桨18和定子侧的涵道体19。
此外,图3示出了作为机翼抬升单元14的另外的组件的板条单元20、21,即上部板条单元20和下部板条单元21。
在起飞和降落时,这两个板条单元20、21打开并且释放由涵道螺旋桨17的涵道体19限定的用于流通的流动通道22。
相反,尤其在起飞后并且降落前的常规飞行运行中不需要机翼抬升单元14时,则板条单元20、21关闭并且封闭相应的涵道螺旋桨17的涵道体19的流动通道22。
如已经阐明的,涵道螺旋桨17相应地具有转子侧的螺旋桨18和定子侧的涵道体19。定子侧的涵道体19限定流经螺旋桨18的空气的流动通道,其中这个流动通道22在涵道螺旋桨17的轴向方向A上延伸。在涵道螺旋桨17的径向方向R上观察,涵道体19在径向外部包围转子或螺旋桨18。
涵道螺旋桨17的涵道体19具有朝向涵道螺旋桨17的螺旋桨18的内壁23以及背离螺旋桨18的外壁24。内壁23和外壁24各自由至少一个纤维增强塑料层、优选地CFK塑料层或替代性地GFK塑料层制成。涵道螺旋桨17的涵道体19的内壁23限定涵道螺旋桨17的用于流经转子18的空气的流动通道22。
优选地,涵道体19的内壁23和外壁24由多个纤维增强塑料层形成,即涵道体19的内壁23由第一数量的层构成,并且外壁24由第二数量的层构成,其中第一数量优选地大于第二数量。于是在内壁23的区域中比在外壁24的区域中有更多个纤维增强塑料层被层压成壁。在内壁23的区域中三个纤维增强塑料层可以形成对应的壁23,并且在外壁24的区域中两个纤维增强塑料层可以形成对应的壁24。
形成涵道螺旋桨17的涵道体19的内壁23和外壁24的纤维增强塑料层优选地是多向纤维增强塑料层。于是纤维增强塑料的纤维在不同的方向上延伸。
在涵道螺旋桨17的涵道体19的内壁23与外壁24之间布置有至少两个、在图5的实施例中三个在涵道螺旋桨17的轴向方向A上毗连的蜂窝芯25、26和27。蜂窝芯27在此在轴向方向A上观察布置在蜂窝芯25与26之间,并且以相应的接触面33、34一方面与蜂窝芯25毗连,并且另一方面与蜂窝芯26毗连。
蜂窝芯25、26和27中的每个蜂窝芯都具有多个蜂窝,其中蜂窝在涵道螺旋桨17的径向方向R或大致在径向方向R上延伸。在图5中,在每个蜂窝芯25、26、27的区域中各示出了一个蜂窝36。在这种在径向方向R上延伸的蜂窝36中,相应蜂窝芯25、26、27的限定蜂窝36的蜂窝壁37在径向方向R上在内壁23与外壁24之间延伸。相应的蜂窝芯25、26和27的蜂窝36在邻接内壁23和外壁24处是开口的。
在涵道螺旋桨17的涵道体19的本身被构造成漏斗状弯曲的入口侧的区段28中,蜂窝36大致在涵道体19以及因此涵道螺旋桨17的径向方向R上延伸。于是,蜂窝36相对于径向方向R倾斜设置。相比之下,在涵道体19以及因此涵道螺旋桨17的出口侧的区段29中,相应的蜂窝体26、27的蜂窝36在径向方向R上延伸。在此,涵道螺旋桨17的涵道体19被构造成管状的或柱状的。
根据本发明,在涵道螺旋桨17或其涵道体19的轴向方向A上彼此毗连的蜂窝芯25、26、27中的至少一个蜂窝芯至少在其与相应邻接的蜂窝芯的相应的接触面33、34区域中由至少一个纤维增强塑料层缠绕或包裹。
在示出的实施例(其中在轴向方向A上看,三个蜂窝芯25、26和27在轴向方向上彼此相继或彼此并排地布置,并且其中蜂窝芯27邻接或毗连蜂窝芯25和蜂窝芯26)中,仅蜂窝芯27至少在其与邻接的蜂窝芯25、26的接触面33、34的区域中由至少一个纤维增强塑料层缠绕或包裹。
特别优选地,毗连的蜂窝芯中的至少一个蜂窝芯(在示出的实施例中是布置在蜂窝芯25和26之间的蜂窝芯27)完全由至少一个纤维增强塑料层缠绕或包裹。
该至少一个纤维增强塑料层为相应的蜂窝芯形成其至少局部的外罩35。
通过在涵道螺旋桨17的轴向方向上毗连的每两个蜂窝芯25、27或26、27中的至少一个蜂窝芯的上述缠绕部或外罩35,一方面可以保证涵道螺旋桨17的涵道体19的较高的刚性以及相关的稳定性,另一方面防止蜂窝芯由于其上的力作用而塌陷或溃缩。这种危险尤其存在于力作用在彼此邻接的蜂窝芯的接触面的区域中。
可以从图5、即图5的细节中看出,布置在蜂窝芯25、26之间的蜂窝芯27完全由外罩35缠绕或包裹,该外罩由至少一个纤维增强塑料层、尤其CFK塑料层或替代性地GFK塑料层制成。塑料在此优选地是多向纤维增强塑料,其中其纤维在不同的方向上延伸。
根据图4和图5,涵道螺旋桨17的涵道体19在轴向位置处具有切口31,该切口容纳进入体32。这个进入体32优选地是泡沫体,其中涵道螺旋桨17的转子或螺旋桨18的转动叶片在运行中可以进入到这个进入体32中,因此在运行中不损坏转子或螺旋桨18的转动叶片。
至少局部地由至少一个纤维增强塑料层缠绕或包裹的蜂窝芯27在此在涵道体19的区域中延伸过进入体32的整个轴向延伸尺寸。在此,如已经阐明的,布置在进入体32的径向外部的蜂窝体27优选地完全由至少一个纤维增强塑料层包裹,以便最佳地从内壁23朝向外壁24的方向传递力。
本发明不仅涉及上述涵道螺旋桨17,而且还涉及这种涵道螺旋桨17的涵道体19。涵道螺旋桨17的涵道体19是飞行器的构件,该涵道体具有由至少一个第一纤维增强塑料层制成的第一壁23和至少一个由至少一个纤维增强塑料层制成的第二壁24,其中在这两个壁23、24之间布置有至少两个蜂窝芯,这些蜂窝芯的蜂窝36在第一壁23与第二壁24之间延伸,并且这些蜂窝相对于蜂窝36的延伸方向垂直地毗连。如上文阐明的,每两个毗连的蜂窝芯中的至少一个蜂窝芯至少在其与邻接的蜂窝芯的相应的接触面33、34的区域中由至少一个纤维增强塑料层缠绕或包裹,其中这个蜂窝芯优选地完全由该至少一个纤维增强塑料层包裹或缠绕。
本发明还涉及飞行器10。飞行器10具有上述的机身11以及接合在机身11上的机翼13。此外,飞行器10具有至少一个根据本发明的涵道螺旋桨17。
该涵道螺旋桨17可以作为机翼抬升单元14的组成部分而被接合在机翼13上,或者作为机鼻抬升单元15的组成部分而被接合在机身11的机鼻16上。
推进单元12也可以具有涵道螺旋桨17。
相应的涵道螺旋桨17如上文详细描述地实施。
尤其,根据本发明的涵道螺旋桨17作为机翼抬升单元14的组成部分而被接合在相应的机翼13上。
Claims (10)
1.一种飞行器的涵道螺旋桨(17),该涵道螺旋桨具有:
转子侧的螺旋桨(18);
定子侧的涵道体(19),该涵道体在径向外部包围该螺旋桨(18)并且限定用于流经该螺旋桨(18)的空气的流动通道(22),
其中该涵道体(19)具有朝向该螺旋桨(18)的内壁(23),该内壁由至少一个纤维增强塑料层制成,
其中该涵道体(19)具有背离该螺旋桨(18)的外壁(24),该外壁由至少一个纤维增强塑料层制成,
其中在该涵道体(19)的内壁(23)与外壁(24)之间布置有至少两个在该涵道螺旋桨(17)的轴向方向(A)上毗连的蜂窝芯(25,26,27),这些蜂窝芯的蜂窝(36)在该涵道螺旋桨的径向方向(R)或大致在径向方向(R)上延伸,
其中在该涵道螺旋桨(17)的轴向方向(A)上毗连的蜂窝芯中的至少一个蜂窝芯(27)至少在其与相应邻接的蜂窝芯(25,26)的相应的接触面(33,34)的区域中由至少一个纤维增强塑料层缠绕或包裹。
2.根据权利要求1所述的涵道螺旋桨(17),其特征在于,这些毗连的蜂窝芯中的至少一个蜂窝芯(27)完全由该至少一个纤维增强塑料层缠绕或包裹。
3.根据权利要求1或2所述的涵道螺旋桨(17),其特征在于,在每两个毗连的蜂窝芯(25,27;26,27)中,该每两个蜂窝芯中的仅一个蜂窝芯(27)至少在其接触面(33,34)的区域中由该至少一个纤维增强塑料层缠绕或包裹。
4.根据权利要求1或2所述的涵道螺旋桨(17),其特征在于,
该涵道体(19)的内壁(23)由第一数量的纤维增强塑料层构成,
该涵道体(19)的外壁(24)由第二数量的纤维增强塑料层构成,
该第一数量大于该第二数量。
5.根据权利要求1或2所述的涵道螺旋桨(17),其特征在于,该涵道体(19)在轴向位置处具有切口(32),该切口容纳进入体(32),该螺旋桨(18)的转动叶片在运行中能够进入到该进入体中,其中至少在其接触面(33,34)的区域中由至少一个纤维增强塑料层缠绕或包裹的蜂窝芯(27)延伸过该进入体(32)的整个轴向延伸尺寸。
6.一种飞行器(10),该飞行器具有:
提供乘客舱的机身(11);
接合在该机身(11)上的机翼(13);
至少一个涵道螺旋桨(17),该至少一个涵道螺旋桨接合在该机身(11)或这些机翼(13)上,
其特征在于,
相应的涵道螺旋桨(17)是根据权利要求1至5之一形成的。
7.根据权利要求6所述的飞行器,其特征在于,相应的涵道螺旋桨(17)接合在一个机翼(13)上。
8.一种飞行器的构件,尤其涵道螺旋桨(17)的涵道体(19),该涵道体具有:
由至少一个纤维增强塑料层制成的第一壁(23);
由至少一个纤维增强塑料层制成的第二壁(24);
至少两个布置在该第一壁(23)与该第二壁(24)之间的蜂窝芯(25,26,27),这些蜂窝芯的蜂窝(36)在该第一壁(23)与该第二壁(24)之间延伸,并且这些蜂窝相对于这些蜂窝(36)的延伸方向垂直地毗连,
其中这些毗连的蜂窝芯中的至少一个蜂窝芯(27)至少在其与相应邻接的蜂窝芯(25,26)的相应的接触面(33,34)的区域中由至少一个纤维增强塑料层缠绕或包裹。
9.根据权利要求8所述的构件,其特征在于,这些毗连的蜂窝芯中的至少一个蜂窝芯(27)完全由该至少一个纤维增强塑料层缠绕或包裹。
10.根据权利要求8或9所述的构件,其特征在于,在每两个毗连的蜂窝芯(25,27;26,27)中,该每两个蜂窝芯中的仅一个蜂窝芯(27)至少在其接触面(33,34)的区域中由该至少一个纤维增强塑料层缠绕或包裹。
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GB1532815A (en) * | 1976-09-27 | 1978-11-22 | Rolls Royce | Rotor blades for ducted fans |
GB2098926A (en) * | 1981-05-26 | 1982-12-01 | Rolls Royce | Honeycomb core with internal septum |
US4362588A (en) * | 1980-07-17 | 1982-12-07 | The United States Of America As Represented By The Secretary Of The Army | Method of fabricating a ducted blanket for a rotor spar |
DE29508107U1 (de) * | 1995-05-17 | 1996-09-12 | Wilhelm Altendorf GmbH & Co KG, 32429 Minden | Schutzhaube |
US20060034682A1 (en) * | 2004-07-14 | 2006-02-16 | Rolls-Royce Plc | Ducted fan with containment structure |
CN101827702A (zh) * | 2007-10-16 | 2010-09-08 | 埃尔塞乐公司 | 用于吸音板的蜂窝芯体结构 |
CN102292210A (zh) * | 2009-02-05 | 2011-12-21 | 埃尔塞乐公司 | 制造涡轮喷气发动机舱用的具有孔格芯体的结构的方法 |
KR101790281B1 (ko) * | 2016-08-04 | 2017-10-26 | 한국과학기술원 | 회전수가 변화되는 상태에서의 음향 라이너를 갖는 덕티드 팬 및 이의 설계 방법 |
CN107584844A (zh) * | 2016-07-08 | 2018-01-16 | 波音公司 | 多层肋饰物及其生产方法 |
CN108945416A (zh) * | 2018-06-28 | 2018-12-07 | 中国直升机设计研究所 | 带涵道升力体的无骨架机身飞行器及机身结构设计方法 |
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DE102008060550B3 (de) | 2008-12-04 | 2010-06-10 | Airbus Deutschland Gmbh | Anordnung zur Verlegung von elektrischen Kabeln im Fußbodenbereich eines Flugzeuges |
DE102018116166B4 (de) | 2018-07-04 | 2023-06-07 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Mantelpropeller und Luftfahrzeug |
DE102018116153B4 (de) | 2018-07-04 | 2021-10-21 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Luftfahrzeug |
DE102018116147A1 (de) | 2018-07-04 | 2020-01-09 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Luftfahrzeug |
DE102018116149B4 (de) | 2018-07-04 | 2023-05-17 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Mantelpropeller und Luftfahrzeug |
DE102018116144B4 (de) | 2018-07-04 | 2022-08-11 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Luftfahrzeug |
DE102018120200A1 (de) | 2018-08-20 | 2020-02-20 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Luftfahrzeug |
DE102018123470B4 (de) | 2018-09-24 | 2022-07-28 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Luftfahrzeug |
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2020
- 2020-10-14 DE DE102020127034.8A patent/DE102020127034A1/de active Granted
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2021
- 2021-10-11 FR FR2110708A patent/FR3115015A1/fr active Pending
- 2021-10-11 CN CN202111182164.7A patent/CN114348241B/zh active Active
- 2021-10-13 US US17/499,964 patent/US20220111954A1/en active Pending
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GB1532815A (en) * | 1976-09-27 | 1978-11-22 | Rolls Royce | Rotor blades for ducted fans |
US4362588A (en) * | 1980-07-17 | 1982-12-07 | The United States Of America As Represented By The Secretary Of The Army | Method of fabricating a ducted blanket for a rotor spar |
GB2098926A (en) * | 1981-05-26 | 1982-12-01 | Rolls Royce | Honeycomb core with internal septum |
DE29508107U1 (de) * | 1995-05-17 | 1996-09-12 | Wilhelm Altendorf GmbH & Co KG, 32429 Minden | Schutzhaube |
US20060034682A1 (en) * | 2004-07-14 | 2006-02-16 | Rolls-Royce Plc | Ducted fan with containment structure |
CN101827702A (zh) * | 2007-10-16 | 2010-09-08 | 埃尔塞乐公司 | 用于吸音板的蜂窝芯体结构 |
CN102292210A (zh) * | 2009-02-05 | 2011-12-21 | 埃尔塞乐公司 | 制造涡轮喷气发动机舱用的具有孔格芯体的结构的方法 |
CN107584844A (zh) * | 2016-07-08 | 2018-01-16 | 波音公司 | 多层肋饰物及其生产方法 |
KR101790281B1 (ko) * | 2016-08-04 | 2017-10-26 | 한국과학기술원 | 회전수가 변화되는 상태에서의 음향 라이너를 갖는 덕티드 팬 및 이의 설계 방법 |
FR3070308A1 (fr) * | 2017-08-25 | 2019-03-01 | Safran Nacelles | Panneau structural et/ou acoustique de nacelle d’ensemble propulsif d’aeronef et procede de fabrication s’y rapportant |
CN108945416A (zh) * | 2018-06-28 | 2018-12-07 | 中国直升机设计研究所 | 带涵道升力体的无骨架机身飞行器及机身结构设计方法 |
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CN114348241B (zh) | 2023-11-14 |
FR3115015A1 (fr) | 2022-04-15 |
US20220111954A1 (en) | 2022-04-14 |
DE102020127034A1 (de) | 2022-04-14 |
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