CN104379326A - 用于生产特别旨在用于航空领域的蜂窝板的方法 - Google Patents
用于生产特别旨在用于航空领域的蜂窝板的方法 Download PDFInfo
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Abstract
本发明涉及一种用于生产特别地用于航空领域的泡沫板的方法,包括以下步骤:提供至少两个泡沫材料块(19a、19b);将所述两个块布置在至少一个干织物板层(21a、2b)上,干织物板层(21a、2b)即所谓的“基板层”,在所述两个块之间保持空间(23);围绕所述两个块(19a、19b)折叠所述基板层(21a、21b)以便包封所述两个块(19a、19b);用至少一个所谓的“增强”织物板层(211a、211b、212a、212b)填充所述两个块(19a、19b)之间的空间(23);在所述增强板层(211a、211b、212a、212b)被插入的侧上,用至少一个所谓的干的或未加工的织物“覆盖”板层(29)覆盖所述基板层(21a、21b);向以此方式生产的组件注入树脂;以及烘烤以此方式生产的组件。
Description
技术领域
本专利申请涉及生产特别旨在用于航空领域的蜂窝板的方法。
背景技术
在航空领域,已经能用蜂窝板生产一定数量的部件。
“蜂窝板”是指由封入在两个刚性外皮之间的蜂窝结构形成的板。
所述蜂窝结构是一种通气结构(aired structure),也就是说,其由并置的蜂房形成。
这样的蜂窝结构可以例如通过聚乙烯泡沫材料或通过用并置小蜂窝形成的蜂窝状型结构形成。
这样的蜂窝板的优点特别在于非常好的阻/重比,使得它们特别适用于航空应用。
而且,当大量的孔穿透外皮之一时,可以获得赫尔姆霍茨箱,从而允许获得声音吸收的效果:因此所述蜂窝板可以应用于飞机涡轮喷气发动机的引擎机舱内部,以便降低这些涡轮喷气发动机发声的强度。
在一定数量的情况下,能够增强这样的蜂窝板的阻力是重要的:例如当要求实现用于飞机涡轮喷气发动机的推力反向门(thrustreversal shutter)时就是这样的情况。
当要求朝着所述涡轮喷气发动机生成的空气流动的飞机部件的前部改变方向时,由推力反向连接杆致动的这样的推力反向门必须能够抵抗非常高的空气压力。
为了达到这个阻力,在形成这些推力反向门的蜂窝板上采取增强措施。
在图1上可以看到现有技术中的这样的推力反向门的第一实施例。
在这个实例中,这个门包括封入在结构化外皮(skin)3和声学外皮5内的蜂窝状结构1,大量的孔穿透外皮。
因此这个推力反向门可以吸收空气流中空气的非常高速的流通导致的噪声的一部分,这个门就安装在所述空气流中。
通常由复合材料生产所述结构化外皮3和声学外皮5,复合材料例如为用聚合树脂得到的玻璃和/或碳纤维的织物板层(ply)。
通过粘合和/或铆接将以金属合金或复合材料形成的角形物7添加到所述结构化外皮3的外部。
在现有技术的第二可替换实例中,如图2所示的,还通过粘合和/或铆接将所述角形物7添加到所述结构化外皮3的内部。
现有技术的这两个可替换实例中的每一个都引发了一定数量的技术问题。
因此,例如,在图1的可替换实例的情形下,所述角形物7阻碍所述推力反向门的外部包围,并且如果发生外部冲击其容易变成分离的。
在图2的可替换实例的情况下,重要的是,用机器来加工所述蜂窝状结构1以便能够将所述角形物7的脚放置和固定在所述结构化外皮3的内面上。
然而,在这两个可替换实例中,当角形物7是复合材料时,它必须在被安装在所述推力反向门上之前预生产,从而必须考虑若干固化周期以形成所述部件的整体。
本发明的目的尤其在于克服这些缺陷。
发明内容
利用一种生产包括夹在第一和第二刚性外皮之间的蜂窝结构的蜂窝板的方法来实现本发明的目的,所述方法的特征在于其包括以下步骤:
-制备至少两块蜂窝材料,
-将所述两块蜂窝材料布置在至少一个称为“基板层”的干织物板层上,在所述两块蜂窝材料之间保持空间,
-围绕所述两块蜂窝材料折叠所述基板层,以便包围(envelop)所述两块蜂窝材料,
-用至少一个“增强”织物板层填充所述两块蜂窝材料之间的空间,
-在所述增强板层已被引入的一侧上用至少一个干的或未加工(fresh)的“覆盖”织物板层覆盖所述基板层;
-向由此获得的组件注入树脂,以及
-固化由此获得的组件。
归因于这个方法,通过在分隔所述蜂窝材料的块的空间中添加织物板层,然后通过在一个操作中固化包围在所述织物板层中的蜂窝材料的块的组件来获得所述蜂窝板的增强。
以此方式,获得了一种增强的蜂窝板,而无需添加其中包含了增强元件的外部部件,且能够在一个单个操作中固化:它以某种方式由“箱”结构组成,具有高度的抵抗性,不包括突起的元件且特别容易生产。
根据按照本发明的这个方法的其他可选特征:
-固化之后穿透所述基板层,以便获得声音吸收板;
-所述增强板层通过所述基板层的至少一个末端的剩余长度形成;
-所述增强板层通过所述基板层的两个末端的剩余长度形成;
-所述增强板层由不同于所述基板层的板层形成;
-所述增强板层由干织物形成;
-所述增强板层用未加工织物形成;
-若干基板层被叠置;
-若干增强板层被叠置;
-若干覆盖板层被叠置;
-使用通过浸渍(infusion)的树脂注入方法。
本发明还涉及根据前述方法获得的蜂窝板,以及装备有至少一个根据前述蜂窝板的用于飞机涡轮喷气发动机的引擎机舱。
附图说明
根据下面的描述并通过研究附图,本发明的其他特征和优点将变得清楚明白,在附图中:
-图1和2是本说明书导言中描述的现有技术的增强蜂窝板的两个可替换实施例的立体图,
-图3和4分别是利用根据本发明的方法实现的推力反向门的机翼上表面的立体图和下表面的立体图,
-图5至7是根据本发明方法第一实施例生产板的不同步骤的截面示意图,以及
-图8是根据本发明方法的第二实施例实现的蜂窝板的截面视图。
在这一组图上,相同或相似的附图标记标明相同或相似的构件或构件的组件。
具体实施方式
现在参照图3和4,其上表示了推力反向门9,旨在为飞机装备推力反向器。
这个推力反向门9具有轻微弯曲的梯形板(trapezoidal plate),其包括机翼的上表面11和机翼的下表面13。
机翼的下表面13是所述门9的旨在与冷空气流动接触的面,所述冷空气流动是由涡轮喷气发动机风扇在直接喷射模式和反向喷射模式生成的。
在直接喷射模式中,机翼的下表面13形成所述推力反向器的冷空气流的外壁,并允许这个冷空气流向着所述涡轮喷气发动机下行流动,因此提供飞机推进所要求的推力。
在反向喷射模式中,所述推力反向门9阻碍冷空气流,使得机翼的下表面13将所述冷空气流动的主要部分重新导向为向着所述推力反向器上行流动,从而允许有助于飞机着陆期间的制动。
因此,应当理解,机翼的下表面13是反向门9的“起作用”的表面,也就是说,该表面应当展现出令人满意的空气动力学和/或声音吸收特征。
值得注意的是,本身已知地,这些直接喷射和反向喷射位置之间的反向门9的致动是由所述推力反向连接杆15触发的。
所述推力反向门9根据本发明的方法实现,并因此包括按照根据本发明的方法实现的内部增强元件17a,17b,后面将会描述。
参考图5、6和7,其上可以看到生产门9的不同步骤,即图4的切割线V-V的区域。
如在图5上可以看到的,开始是在干织物的板层21上设置蜂窝材料的两个块19a和19b,在这两个块19a和19b之间保持空间23,所述蜂窝材料例如为蜂窝状结构。
值得注意的是,这里的“板层”是指纤维织物的层,例如碳或玻璃纤维,旨在用热聚合树脂浸渍(impregnate)。
一旦如图5所示所述两个块19a和19b被置于基板层21上,这个基板层21的两个末端25a和25b被折叠,以便包围这两个蜂窝材料块19a和19b。
在随后的步骤中,如图6上可见的,多个“增强”板层被插入在所述两个块19a和19b之间保持的空间23中。
值得注意的是,这些板层27可以是干板层,也就是说,不带有树脂的纤维的板层,或者这些板层27可以是未加工的板层,也就是说,预先浸渍了树脂的板层。
一旦这些增强板层27被插入在空间23中,这样形成的增强板层27被引入的组件的面被至少一个、优选地多个29a、29b干“覆盖”板层或未加工的“覆盖”板层29a、29b覆盖。
然后,这样获得的组件被注入诸如聚酰亚胺之类的聚合树脂,这样注入的组件在高压釜中固化,以便聚合树脂并使所述组件硬化。
所述树脂注入方法可以例如是本身已知的树脂传递成型RTM类型的方法。
如根据前述可以理解的,刚刚描述的实现所述蜂窝板的增强27的方法非常容易实施。
实际上,这个方法在于按照合适的顺序和几何关系放置板层,然后一旦实现这个放置便在一个单个步骤中固化这个组件。
与现有技术的增强蜂窝板相反,不需要对蜂窝状材料的块19a、19b进行机器加工;也不需要粘接或铆接,并且没有增强元件超出末端部分的包封容量。
显然地,基板层21、增强板层27和覆盖板层29a、29b的数量决不限于所给出的实施例:实际上叠置的板层的数量可以根据需要和所寻求的机械特征而变化。
在图8上展示的实施例中,使用了两个基板层21a、21b以及单个覆盖板层29。
与前面的实施例不同的是,使用了剩余长度,分别是基板层21a和基板层21b的211a、211b和212a、212b,所述剩余长度在分隔所述两个蜂窝材料的块19a和19b的空间23中以U形状布置。
因此,在这个实例中,所述基板层21a和21b的剩余长度可以是之前实施例的增强板层27的替代。
如果要求这样获得的蜂窝板实现声音吸收功能,正如一般的所述推力反向门的情况,所述基板层21或21a、21b当然可以被刺穿,以使蜂窝材料块19a和19b的小蜂窝可以与旨在沿着所述推力反向门的机翼的下表面13通过的冷空气连通。
如本身已知的,每个蜂窝材料块19a、19b其自身可以由蜂窝状结构的堆叠构成,以便实现最优的声音吸收(SDOF或DDOF声音吸收结构,例如单自由度、双自由度,这本身是已知的)。
显然,本发明决不限于仅通过实例描述、呈现和提供的实施例。
因此,归因于根据本发明的方法实现的所述蜂窝板可以装备用于飞机涡轮喷气发动机的引擎机舱的任何其他部件,并展现或不展现声音吸收特征。
根据本发明的方法还可以用于生产旨在用于飞机的不同于引擎机舱的部件的蜂窝板。
Claims (13)
1.用于生产包括夹在第一刚性外皮和第二刚性外皮之间的蜂窝结构的蜂窝板的方法,其特征在于其包括以下步骤:
-制备至少两块蜂窝材料(19a、19b),
-将所述两块蜂窝材料布置在至少一个称为“基板层”的干织物的板层(21;21a、21b)上,在所述两块蜂窝材料之间保持空间(23),
-围绕所述两块蜂窝材料(19a、19b)折叠所述基板层(21;21a、21b),以包围所述两块蜂窝材料,
-用至少一个“增强”织物板层(27;211a、211b、212a、212b)填充所述两块蜂窝材料(19a、19b)之间的空间(23),
-在所述增强板层(27、27;211a、211b、212a、212b)已被引入的一侧上用至少一个干的或未加工的“覆盖”织物板层(29;29a、29b)覆盖所述基板层(21;21a、21b);
-向由此获得的组件注入树脂,以及
-固化由此获得的组件。
2.根据权利要求1的方法,其中固化之后穿透所述基板层(21;21a、21b),以获得声音吸收板。
3.根据权利要求1或2中任一个的方法,其中通过所述基板层(21a、21b)的至少一个末端的剩余长度(211a、211b、212a、212b)形成所述增强板层。
4.根据权利要求2的方法,通过所述基板层(21a、21b)的两个末端的剩余长度(211a、211b、212a、212b)形成所述增强板层。
5.根据权利要求1或2中任一个的方法,其中通过不同于所述基板层(21)的板层(27)形成所述增强板层。
6.根据权利要求5的方法,其中用干织物形成所述增强板层(27)。
7.根据权利要求5的方法,其中用未加工织物形成所述增强板层(27)。
8.根据前述权利要求中任一个的方法,其中若干基板层(21a、21b)被叠置。
9.根据前述权利要求中任一个的方法,其中若干增强板层(29a、29b)被叠置。
10.根据前述权利要求中任一个的方法,其中若干覆盖板层(29a、29b)被叠置;
11.根据前述权利要求中任一个的方法,其中使用通过浸渍的树脂注入方法。
12.一种根据前述权利要求中任一个的方法获得的蜂窝板。
13.一种装备有至少一个根据权利要求12的蜂窝板的用于飞机涡轮喷气发动机的引擎机舱。
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PCT/FR2013/051346 WO2013186476A1 (fr) | 2012-06-12 | 2013-06-11 | Procédé de fabrication de panneaux cellulaires, destinés notamment au domaine de l'aéronautique |
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CN107533837A (zh) * | 2015-05-11 | 2018-01-02 | 赫克赛尔公司 | 具有多个自由度的声学结构 |
CN113942260A (zh) * | 2020-07-16 | 2022-01-18 | 何昌宪 | 安全头盔胶壳强化的制造方法及由所述方法制成的头盔结构 |
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US11315538B2 (en) * | 2017-12-13 | 2022-04-26 | The Boeing Company | Anti-resonant panels |
US11261825B2 (en) * | 2018-09-24 | 2022-03-01 | Rohr, Inc. | Thermoplastic acoustic blocker door |
FR3096610B1 (fr) * | 2019-06-03 | 2023-05-12 | Airbus Operations Sas | Procédé de fabrication d’une structure travaillante d’atténuation acoustique, structure d’atténuation acoustique obtenue à partir dudit procédé et aéronef comprenant une telle structure d’atténuation acoustique |
CN112407236B (zh) * | 2020-10-27 | 2022-10-25 | 成都飞机工业(集团)有限责任公司 | 一种蜂窝夹芯石墨烯隐身前缘及其加工方法 |
CN117067637B (zh) * | 2023-09-13 | 2023-12-19 | 哈尔滨远驰航空装备有限公司 | 一种树脂基复合蜂窝加强结构及其成型方法 |
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US20090155524A1 (en) * | 2007-12-13 | 2009-06-18 | Rapp Robert A | Composite panel and method of manufacturing the same |
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FR2940176B1 (fr) * | 2008-12-22 | 2011-02-11 | Aircelle Sa | Procede de fabrication d'un panneau d'attenuation acoustique, notamment pour l'aeronautique |
DE102010035958B8 (de) * | 2010-08-31 | 2012-07-05 | Airbus Operations Gmbh | Vorrichtung und Verfahren zur Herstellung eines Bauteils sowie Flugzeugstrukturbauteil |
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WO1984004940A1 (en) * | 1983-06-10 | 1984-12-20 | Haller Gmbh Fahrzeugbau | Building element, method for the manufacturing thereof and utilization |
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Cited By (3)
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CN104379326B (zh) | 2016-04-27 |
WO2013186476A1 (fr) | 2013-12-19 |
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US20150090524A1 (en) | 2015-04-02 |
BR112014030971A2 (pt) | 2017-06-27 |
CA2875489A1 (fr) | 2013-12-19 |
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FR2991625A1 (fr) | 2013-12-13 |
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