CN114889233A - 一种轻型翼肋及其成型方法 - Google Patents

一种轻型翼肋及其成型方法 Download PDF

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CN114889233A
CN114889233A CN202210462014.XA CN202210462014A CN114889233A CN 114889233 A CN114889233 A CN 114889233A CN 202210462014 A CN202210462014 A CN 202210462014A CN 114889233 A CN114889233 A CN 114889233A
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reinforcing layer
carbon fiber
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fiber composite
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王玉凯
郭红军
涂尚平
陈帅
耿强华
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Changzhou Qifu Antai Composite Technology Co ltd
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Abstract

本发明属于机翼技术领域，尤其涉及一种轻型翼肋成型方法，包括如下步骤：S1：将第一碳纤维复合板、泡沫芯板和第二碳纤维复合板依次铺贴，固化后获得泡沫夹芯板材；S2：将泡沫夹芯板材加工出若干翼肋本体，并在翼肋本体上加工出管梁通过孔和减重孔；S3：在翼肋本体的一面且在管梁通过孔的外周依次铺贴胶膜和第一加强层后压实固化；利用铺贴样板，再在翼肋本体的另一面且在管梁通过孔的外周依次铺贴胶膜和第二加强层后压实固化；S4：在翼肋本体的边缘，以及其管梁通过孔和减重孔的边缘均依次铺贴胶膜和包边，压实固化后获得翼肋预制件；S5：翼肋预制件二次固化获得该轻型翼肋。

Description

一种轻型翼肋及其成型方法
技术领域
本发明属于机翼技术领域，尤其涉及一种轻型翼肋及其成型方法。
背景技术
翼肋是飞机机翼的一个重要构成之一，机翼的横向受力骨架，一般与翼型的形状一致，用来支持飞机机翼的蒙皮，维持机翼的剖面形状。碳纤维复合材料具有比重小、刚度大、强度高、耐腐蚀等优点，已经在航空航天等高端领域以及民用领域普及。为了结构减重、提高续航里程，如今无人机的机翼、襟副翼，大型轮船的船帆都采用了碳纤维复合材料，其中大多采用密肋结构。如申请号为CN202110112090.3，公开的一种复合材料加强翼肋的成型模具及成型方法，现有翼肋多为缘条腹板式，因为考虑空气动力学，机翼的形状都会发生尺寸的变化，因此翼肋的大小多不相同，所以缘条腹板式的碳纤维复合材料翼肋均需设计不同的成型模具，成型费用会急剧增加，成型效率较低，且成型后翼肋的重量大。
发明内容
为解决现有技术存在的翼肋重量大，且因翼肋的大小不同，翼肋需要不同的成型模具，成型费用高和成型效率低的问题，本发明提供一种轻型翼肋及其成型方法。
为解决上述技术问题，本发明所采用的技术方案如下，一种轻型翼肋，包括翼肋本体、第一加强层和第二加强层，所述翼肋本体包括第一碳纤维复合层、泡沫芯层和第二碳纤维复合层，所述第一加强层、第一碳纤维复合层、泡沫芯层、第二碳纤维复合层和第二加强层依次固定连接；所述翼肋本体上贯穿有管梁通过孔和减重孔；所述翼肋本体的边缘、管梁通过孔的边缘和减重孔的边缘均设置有包边；所述第一加强层和第二加强层均位于管梁通过孔的外周。
作为优选，所述第一加强层、第一碳纤维复合层、泡沫芯层、第二碳纤维复合层和第二加强层的相邻层结构之间均通过胶膜固定连接。确保相邻层结构之间固定连接的可靠性。
进一步地，所述胶膜为一个整体胶膜，或者所述胶膜包括多个块状胶膜，多个所述块状胶膜采用搭接形式铺设，其搭接量为2mm～6.5mm。确保胶膜铺设的可靠性，以及确保胶膜的粘附性。
作为优选，所述第一加强层、第二加强层和包边的材料均为碳纤维复合材料；所述第一碳纤维复合层和第二碳纤维复合层均由多层碳纤维预浸料固化而成。确保第一加强层、第二加强层、第一碳纤维复合层和第二碳纤维复合层发挥碳纤维复合材料的优点。
进一步地，所述泡沫芯层的厚度范围为3mm～50mm；所述泡沫芯层的密度范围为30kg/m3～200kg/m3。避免在较大的固化压力下，泡沫芯层被压溃，从而可以保证该轻型翼肋的整体质量。
一种用于上述任一种所述的轻型翼肋的轻型翼肋成型方法，包括如下步骤：
S1：将第一碳纤维复合板、泡沫芯板和第二碳纤维复合板依次铺贴，固化后获得泡沫夹芯板材；
S2：将泡沫夹芯板材加工出若干翼肋本体，并在翼肋本体上加工出管梁通过孔和减重孔；
S3：在翼肋本体的一面且在管梁通过孔的外周依次铺贴胶膜和第一加强层后压实固化；再在翼肋本体的另一面且在管梁通过孔的外周依次铺贴胶膜和第二加强层后压实固化；
S4：在翼肋本体的边缘，以及其管梁通过孔和减重孔的边缘均依次铺贴胶膜和包边，压实固化后获得翼肋预制件；
S5：翼肋预制件二次固化获得该轻型翼肋。
作为优选，在所述步骤S3中，铺贴第二加强层时，翼肋本体放置在铺贴样板上，铺贴样板和第一加强层配合平铺在第一碳纤维复合层的底面，使翼肋预制件处于一个平面上，且完成步骤S4获得翼肋预制件后，铺贴样板可脱离翼肋预制件。保证翼肋预制件处于一个平面上，确保在铺贴固化过程中翼肋本体不会发生悬空从而产生变形，可以保持该轻型翼肋的形状。
作为优选，在所述步骤S1中，泡沫芯板与第一碳纤维复合板和第二碳纤维复合板之间均铺贴有胶膜。提高泡沫芯板与第一碳纤维复合板和第二碳纤维复合板之间固定连接的可靠性。
进一步地，在所述步骤S3中，采用真空压实，压实操作的真空值不小于0.085MPa并保持至少10min，若第一加强层或第二加强层与翼肋本体不贴合时，采用热风枪进行加温，使两者之间贴合；在所述步骤S3中，还需对翼肋预制件的第一加强层和第二加强层进行裁剪修边，使第一加强层和第二加强层的边界与翼肋本体对齐整。提高第一加强层和第二加强层铺贴的成型可靠性和成型精度。
进一步地，在所述步骤S5中，先将平铺放置的若干翼肋预制件真空封装，并在真空封装空间内均匀设置至少两个热电偶，再将翼肋预制件放入热压罐抽真空，加热进行二次固化获得该轻型翼肋。可以核查翼肋预制件的升降温速率，保证该轻型翼肋的质量。
有益效果：
1、本发明的轻型翼肋，整体结构为泡沫夹芯式，第一碳纤维复合层和第二碳纤维复合层的设置，开设减重孔，以及通过第一加强层和第二加强层局部加强，可以极大的提高结构效率，减轻结构重量，符合无人机轻量化的要求；在边缘开孔包边，翼肋本体的边缘、管梁通过孔的边缘和减重孔的边缘均设置有包边，有效防止泡沫芯层长时间裸露在外发生吸湿，造成强度损失。
2、本发明的轻型翼肋的成型方法，下料、铺贴方便，可以批量化的成型，明显的提高成型效率，且精度高；将翼肋本体作为第一加强层、第二加强层和包边铺贴的模具，节省了大量模具，缩减了开发周期，明显的降低了生产成本。
附图说明
为了更清楚地说明本发明实施例的技术方案，下面将对实施例描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域的普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其它附图。
图1是本发明轻型翼肋的立体结构示意图；
图2是本发明轻型翼肋的另一角度立体结构示意图；
图3是本发明轻型翼肋的爆炸示意图；
图4是本发明轻型翼肋成型时铺贴样板的设置位置示意图；
图5是本发明轻型翼肋成型时铺贴样板脱离的立体结构示意图；
图中：1、翼肋本体，11、第一碳纤维复合层，12、泡沫芯层，13、第二碳纤维复合层，14、管梁通过孔，15、减重孔，2、第一加强层，3、第二加强层，4、包边，5、铺贴样板。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。以下对至少一个示例性实施例的描述实际上仅仅是说明性的，决不作为对本发明及其应用或使用的任何限制。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其它实施例，都属于本发明保护的范围。
实施例
如图1～3所示，一种轻型翼肋，包括翼肋本体1、第一加强层2和第二加强层3，所述翼肋本体1包括第一碳纤维复合层11、泡沫芯层12和第二碳纤维复合层13，所述第一加强层2、第一碳纤维复合层11、泡沫芯层12、第二碳纤维复合层13和第二加强层3依次固定连接；所述翼肋本体1上贯穿有管梁通过孔14和减重孔15；所述翼肋本体1的边缘、管梁通过孔14的边缘和减重孔15的边缘均设置有包边4；所述第一加强层2和第二加强层3均位于管梁通过孔14的外周。
为了确保相邻层结构之间固定连接的可靠性，在本实施例中，所述第一加强层2、第一碳纤维复合层11、泡沫芯层12、第二碳纤维复合层13和第二加强层3的相邻层结构之间均通过胶膜固定连接；所述胶膜为一个整体胶膜，或者所述胶膜包括多个块状胶膜，多个所述块状胶膜采用搭接形式铺设，其搭接量为2mm～6.5mm。
为了确保该轻型翼肋的结构强度，保证该轻型翼肋的整体质量，在本实施例中，所述第一加强层2、第二加强层3和包边4的材料均为碳纤维复合材料；所述第一碳纤维复合层11和第二碳纤维复合层13均由多层碳纤维预浸料固化而成；所述泡沫芯层12的厚度范围为3mm～50mm；所述泡沫芯层12的密度范围为30kg/m3～200kg/m3。
如图1～5所示，一种用于成型上述的轻型翼肋的轻型翼肋成型方法，包括如下步骤：
S1：先裁剪下料获得第一碳纤维复合板、泡沫芯板和第二碳纤维复合板，将第一碳纤维复合板、泡沫芯板和第二碳纤维复合板在平板工装(平台)上依次铺贴，固化后获得泡沫夹芯板材；本实施例的泡沫芯板与第一碳纤维复合板和第二碳纤维复合板之间均铺贴有胶膜；
S2：将泡沫夹芯板材在CNC五轴数控机床上加工出若干翼肋本体1，并在翼肋本体1上加工出管梁通过孔14和减重孔15；
S3：将翼肋本体1放置在平板工装(平台)上，在翼肋本体1的一面且在管梁通过孔14的外周依次铺贴胶膜和第一加强层2后压实固化；将翼肋本体1翻面，再在翼肋本体1的另一面且在管梁通过孔14的外周依次铺贴胶膜和第二加强层3后压实固化；即，将翼肋本体1作为第一加强层2和第二加强层3铺贴的模具；
S4：在翼肋本体1的边缘，以及其管梁通过孔14和减重孔15的边缘均依次铺贴胶膜和包边4，压实固化后获得翼肋预制件；即，将翼肋本体1作为包边4铺贴的模具；
S5：翼肋预制件二次固化获得该轻型翼肋。
为了有效防止铺贴第一加强层2和第二加强层3时翼肋本体1变形，在本实施例中，在所述步骤S3中，铺贴第二加强层3时，翼肋本体1放置在铺贴样板5上，铺贴样板5和第一加强层2配合平铺在第一碳纤维复合层11的底面，使翼肋预制件处于一个平面上，确保在铺贴固化过程中翼肋本体1不会发生悬空从而产生变形，可以保持该轻型翼肋的形状；且完成步骤S4获得翼肋预制件后，铺贴样板5可脱离翼肋预制件，如图4和图5所示，具体地，在本实施例中，铺贴样板5和包边4之间具有间隙。
具体地，在本实施例中，在所述步骤S3中，采用真空压实，压实操作的真空值不小于0.085MPa并保持至少10min，若第一加强层2或第二加强层3与翼肋本体1不贴合时，采用热风枪进行加温，使两者之间贴合；在所述步骤S3中，还需对翼肋预制件的第一加强层2和第二加强层3进行裁剪修边，使第一加强层2和第二加强层3的边界与翼肋本体1对齐整。
具体地，在本实施例中，在所述步骤S5中，先将平铺放置的若干翼肋预制件真空封装，并在真空封装空间内均匀设置至少两个热电偶，再将翼肋预制件放入热压罐抽真空，加热进行二次固化获得该轻型翼肋，其中热电偶可以核查翼肋预制件的升降温速率，保证该轻型翼肋的质量。
以上，仅为本发明较佳的具体实施方式，但本发明的保护范围并不局限于此，任何熟悉本技术领域的技术人员在本发明揭露的技术范围内，根据本发明的技术方案及其发明构思加以等同替换或改变，都应涵盖在本发明的保护范围之内。

Claims (10)

1.一种轻型翼肋，其特征在于：包括翼肋本体(1)、第一加强层(2)和第二加强层(3)，所述翼肋本体(1)包括第一碳纤维复合层(11)、泡沫芯层(12)和第二碳纤维复合层(13)，所述第一加强层(2)、第一碳纤维复合层(11)、泡沫芯层(12)、第二碳纤维复合层(13)和第二加强层(3)依次固定连接；所述翼肋本体(1)上贯穿有管梁通过孔(14)和减重孔(15)；所述翼肋本体(1)的边缘、管梁通过孔(14)的边缘和减重孔(15)的边缘均设置有包边(4)；所述第一加强层(2)和第二加强层(3)均位于管梁通过孔(14)的外周。
2.根据权利要求1所述的轻型翼肋，其特征在于：所述第一加强层(2)、第一碳纤维复合层(11)、泡沫芯层(12)、第二碳纤维复合层(13)和第二加强层(3)的相邻层结构之间均通过胶膜固定连接。
3.根据权利要求2所述的轻型翼肋，其特征在于：所述胶膜为一个整体胶膜，或者所述胶膜包括多个块状胶膜，多个所述块状胶膜采用搭接形式铺设，其搭接量为2mm～6.5mm。
4.根据权利要求1所述的轻型翼肋，其特征在于：所述第一加强层(2)、第二加强层(3)和包边(4)的材料均为碳纤维复合材料；所述第一碳纤维复合层(11)和第二碳纤维复合层(13)均由多层碳纤维预浸料固化而成。
5.根据权利要求1所述的轻型翼肋，其特征在于：所述泡沫芯层(12)的厚度范围为3mm～50mm；所述泡沫芯层(12)的密度范围为30kg/m3～200kg/m3。
6.一种用于成型权利要求1～5任一项所述的轻型翼肋的轻型翼肋成型方法，其特征在于：包括如下步骤：
S1：将第一碳纤维复合板、泡沫芯板和第二碳纤维复合板依次铺贴，固化后获得泡沫夹芯板材；
S2：将泡沫夹芯板材加工出若干翼肋本体(1)，并在翼肋本体(1)上加工出管梁通过孔(14)和减重孔(15)；
S3：在翼肋本体(1)的一面且在管梁通过孔(14)的外周依次铺贴胶膜和第一加强层(2)后压实固化；再在翼肋本体(1)的另一面且在管梁通过孔(14)的外周依次铺贴胶膜和第二加强层(3)后压实固化；
S4：在翼肋本体(1)的边缘，以及其管梁通过孔(14)和减重孔(15)的边缘均依次铺贴胶膜和包边(4)，压实固化后获得翼肋预制件；
S5：翼肋预制件二次固化获得该轻型翼肋。
7.根据权利要求6所述的轻型翼肋的成型方法，其特征在于：在所述步骤S3中，铺贴第二加强层(3)时，翼肋本体(1)放置在铺贴样板(5)上，铺贴样板(5)和第一加强层(2)配合平铺在第一碳纤维复合层(11)的底面，使翼肋预制件处于一个平面上，且完成步骤S4获得翼肋预制件后，铺贴样板(5)可脱离翼肋预制件。
8.根据权利要求6或7所述的轻型翼肋的成型方法，其特征在于：在所述步骤S1中，泡沫芯板与第一碳纤维复合板和第二碳纤维复合板之间均铺贴有胶膜。
9.根据权利要求6或7所述的轻型翼肋的成型方法，其特征在于：在所述步骤S3中，采用真空压实，压实操作的真空值不小于0.085MPa并保持至少10min，若第一加强层(2)或第二加强层(3)与翼肋本体(1)不贴合时，采用热风枪进行加温，使两者之间贴合；在所述步骤S3中，还需对翼肋预制件的第一加强层(2)和第二加强层(3)进行裁剪修边，使第一加强层(2)和第二加强层(3)的边界与翼肋本体(1)对齐整。
10.根据权利要求6或7所述的轻型翼肋的成型方法，其特征在于：在所述步骤S5中，先将平铺放置的若干翼肋预制件真空封装，并在真空封装空间内均匀设置至少两个热电偶，再将翼肋预制件放入热压罐抽真空，加热进行二次固化获得该轻型翼肋。
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