CN107297925B - 一种轻质高强度耐高温腹鳍及成型方法 - Google Patents

一种轻质高强度耐高温腹鳍及成型方法 Download PDF

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CN107297925B
CN107297925B CN201710453751.2A CN201710453751A CN107297925B CN 107297925 B CN107297925 B CN 107297925B CN 201710453751 A CN201710453751 A CN 201710453751A CN 107297925 B CN107297925 B CN 107297925B
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刘庆
鲜于运坤
洪坤
汪文龙
胡保朝
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General Designing Institute of Hubei Space Technology Academy
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Abstract

本发明公开了一种轻质高强度耐高温腹鳍及成型方法，腹鳍包括蒙皮、夹芯、前连接头、后连接头、防热层。腹鳍为采用碳布/双马复合材料蒙皮、PMI泡沫夹芯、铝合金接头的泡沫夹层结构，具有高强轻质的优点；借助碳布/双马复合材料、PMI泡沫夹芯的耐温性，同时通过在前缘热严酷部位增加玻璃布的方式，使腹鳍具有耐高温的优点；通过采用RTM整体固化成型，通过设计前端固连，后端简支的安装结构，具有快速安装和拆卸的优点。本发明的腹鳍具有轻质高强耐高温以及低成本、快速制备、快速安装和拆卸的优点，特别适用于对轻质化要求高的耐高温翼面结构。

Description

一种轻质高强度耐高温腹鳍及成型方法
技术领域
本发明属于飞行器翼面结构设计技术领域，具体涉及一种轻质高强度耐高温腹鳍及成型方法。
背景技术
腹鳍是飞行器翼面的一种，是重要的气动结构件，位于飞行器尾部，侧滑时起增加飞行器航向稳定性、保持平衡的作用。腹鳍一方面需要有足够的强度和刚度，满足承载的功能；另一方面，随着飞行器飞行速度提高、轻质要求提升，对翼面结构的轻质耐温提出更高的要求。
翼面结构沿着轻质高强度耐高温的方向发展，翼面发展大致经历了实心板式翼面、整体夹芯式舵翼面、蒙皮骨架式舵翼面和夹层结构舵翼面四个阶段。
发明内容
本发明提供一种轻质高强度耐高温腹鳍及成型方法，具有低密度、高强度、耐高温、结构简单、制备周期短、成本低的优点，使腹鳍能够更好满足飞行器对腹鳍的使用要求。
一种轻质高强度耐高温腹鳍及成型方法，采用泡沫夹层复合材料结构，包括蒙皮、夹芯、前连接头、后连接头和玻璃布，其特征在于：
蒙皮选用碳布/双马复合材料，完全包裹在夹芯、前连接头、后连接头、玻璃钢的外表面，提供腹鳍所需的力学性能，是腹鳍的主要承力构件，同时满足腹鳍的耐温性能要求；
夹芯采用PMI泡沫材料，全尺寸填充于夹层内部，并与金属连接头嵌套配合。夹芯一方面作为结构单元，提升整体刚度、结构稳定性，传递接头的载荷；另一方面作为芯模，便于蒙皮碳布的铺层和固化过程中尺寸的稳定性；并且满足腹鳍的耐温性能要求；
前接头和后接头采用铝合金材料，为腹鳍与飞行器的机械安装接口。前接头和后接头设计为薄壳结构，***到泡沫夹芯中，并与蒙皮设计较大的接触面积，通过与泡沫的嵌入结构和蒙皮的粘接面实现载荷传递；
为提升热环境严酷的腹鳍前缘耐温性，在腹鳍前缘的蒙皮和夹芯之间增加无碱玻璃布。
进一步地，所述蒙皮与前接头、后接头和夹芯界面层之间增加胶膜层，提升不同材料之间的热匹配性能。
进一步地，在所述腹鳍前缘的蒙皮和夹芯之间增加的无碱玻璃布通过铺层在夹芯上，浸渍双马树脂后高温固化成型，玻璃布铺层厚度为1～3mm，可有效提升腹鳍前缘的耐温性能。
进一步地，所述蒙皮采用T300碳布铺层设计，交叉铺层，在边缘处允许搭接，蒙皮厚度为1～3mm，根弦搭接蒙皮厚度为2～6mm。
进一步地，所述腹鳍通过前接头的4个光孔和后接头的倒勾结构实现与飞行器的机械安装，前端固连，后端简支的方式具有快速安装和拆卸的优点。
更进一步地，所述腹鳍采用树脂传递模塑成型(RTM)工艺整体制备，通过将加工后的夹芯、前接头和后接头嵌套到位后，在外表面铺层碳布后将产品放入模具中注塑树脂高温固化成型，具体如下：
(a)夹芯加工:用PMI泡沫加工成整体实心结构；
(b)前连接头和后连接头机械加工成型；
(c)前连接头和后连接头与夹芯嵌套组合通过树脂胶结成结构单元；
(d)在夹芯前缘铺层玻璃布；
(e)在外表面铺层碳布后将产品放入模具中注塑树脂高温固化成型。
本发明的技术效果体现在：
本发明中，蒙皮是实现承载防热的零件；夹芯提供腹鳍的刚度和稳定性，并作为芯模利于碳布铺层；前接头和后接头是实现腹鳍与飞行器安装的零件，设计合理的结构利于蒙皮、夹芯与接头之间的受力传递；腹鳍前缘处的玻璃布具有提升前缘耐温性的能力；蒙皮、接头、夹芯界面层之间的胶膜是协调热变形，提高热匹配的结构。
本发明中，通过采用碳布/双马复合材料蒙皮、PMI泡沫夹芯、铝合金接头的泡沫夹层结构，具有高强轻质的优点；借助碳布/双马复合材料、PMI泡沫夹芯的耐温性，同时通过在前缘热严酷部位增加玻璃布的方式，使腹鳍具有耐高温的优点；通过采用RTM整体固化成型，具有制备周期短、低成本的优点；通过设计前端固连，后端简支的安装结构，具有快速安装和拆卸的优点。
附图说明
图1为本发明实施例腹鳍的结构示意图
图2为本发明实施例腹鳍前接头的外形示意图
图3为本发明实施例腹鳍后接头的外形示意图
具体实施方式
以下结合附图和具体实施例对本发明的一种轻质高强度耐高温腹鳍及成型方法作进一步的详细描述。
如图1所示的一种轻质高强度耐高温腹鳍及成型方法，采用碳布/双马复合材料蒙皮、PMI泡沫夹芯、铝合金接头的泡沫夹层结构，通过采用RTM整体固化成型。本发明的腹鳍包括蒙皮1、夹芯2、后接头3、前接头4、玻璃布5。
蒙皮1采用碳布/双马复合材料，具有耐高温、高比强度、高比刚度、工艺性好等优点，是理想的轻质面板材料。蒙皮1完全包裹在腹鳍的外表面，提供腹鳍所需的力学性能，是腹鳍的主要承力构件，同时满足腹鳍的耐温性能要求。蒙皮1选用T300碳布，铺层在夹芯2上，铺层顺序由内向外为[0°/90°/0°/0°/90°/0°]，其中最外层厚度为0.2mm，里面各层厚度为0.3mm，铺层完成后通过双马树脂RTM成型，蒙皮厚度为2mm，根弦搭接蒙皮厚度为4mm。
夹芯2选用PMI泡沫，具有耐温性高、密度低、强度高、刚度高、高温耐蠕变性能好等优点，是理想的泡沫夹芯材料。夹芯2设计为拼接全尺寸实心结构，前接头4和后接头3嵌套入夹芯2中，后接头3和前接头4与夹芯2有良好的匹配性，玻璃布5铺层到夹芯2前缘部位。夹芯一方面作为结构单元，提升整体刚度、结构稳定性，传递接头的载荷；另一方面作为芯模，便于蒙皮碳布的铺层和固化过程中尺寸的稳定性；再者满足腹鳍的耐温性能要求；
如图1所示，后接头3位于腹鳍的后端部位，实现腹鳍后端与飞行器连接的功能。后接头3选用铝合金材料，嵌入到夹芯2中，并与蒙皮1通过树脂胶结。
如图3所示，后接头3包括薄壳3a、倒勾3b等结构特征，薄壳3a增大与蒙皮1的接触面积，并嵌套入夹芯2匹配的槽中，实现载荷的传递，倒勾3b实现飞行器与腹鳍后端的简支连接与限位。
如图1所示，前接头4位于腹鳍的前端部位，实现腹鳍前端与飞行器连接的功能。前接头4选用铝合金材料，嵌入到夹芯2中，并与蒙皮1通过树脂胶结。
如图2所示，前接头4包括薄壳特征4a、4b、4c和光孔4d，薄壳特征增大与蒙皮1的接触面积，并嵌套入夹芯2匹配的槽中，实现载荷的传递。光孔4d是腹鳍与飞行器的前端固定接口，通过4个M10螺栓与飞行器支座连接。
腹鳍前缘部位增加玻璃布5，以提升热环境严酷的前缘局部位置的耐温性。玻璃布5铺层到夹芯2的前缘位置，铺层厚度为2mm，通过双马树脂高温固化成型。
为提升腹鳍蒙皮1、夹芯2、后接头3和前接头4界面处的热匹配性，在界面层增加一层柔韧性的胶膜层，作为热应力缓冲层，避免腹鳍蒙皮1与夹芯2、后接头3和前接头4由于热变形导致的脱粘等缺陷。
腹鳍采用RTM整体成型，首先完成夹芯2、后接头3和前接头4的加工，将后接头3、前接头4嵌套入夹芯2对应的槽内，在夹芯2前缘铺层玻璃布5，在各层的界面粘接胶膜层后，将装配完成后的产品放入模具中，通过注入双马树脂在150℃高温固化后成型，成型后的腹鳍加工4个M10的光孔，即完成腹鳍制备。
具体实施例一种大尺寸轻质高强耐高温腹鳍全长2355mm，高度443mm，厚度40mm，重量10kg，体积密度仅为4×10-7kg/mm3，具有轻质高强的优点；另外，腹鳍大面积使用温度为200℃，前缘使用温度超过300℃；腹鳍结构简单，并采用RTM整体成型，具有制备周期短、成本低的优点。

Claims (4)

1.一种轻质高强度耐高温腹鳍，包括蒙皮、夹芯、前连接头、后连接头和隔热层；其特征在于采用复合材料泡沫夹层结构，用碳布/双马复合材料作蒙皮材质，用PMI泡沫材料作夹芯材质，用无碱玻璃布作隔热层材质，前连接头和后连接头材质为铝合金材料；
其中：所述蒙皮与前连接头、后连接头和夹芯界面层之间有柔韧性胶膜层；
其中：腹鳍前缘的蒙皮和夹芯之间有无碱玻璃布，玻璃布厚度为1～3mm；
其中：蒙皮采用T300碳布铺层，交叉铺层，在边缘处搭接，蒙皮厚度为1～3mm，根弦搭接蒙皮厚度为2～6mm；
其中：前连接头和后连接头设计为薄壳结构，嵌入到夹芯匹配的槽中，与蒙皮有较大的粘接面积，实现载荷的传递。
2.根据权利要求1所述的一种轻质高强度耐高温腹鳍，夹芯可分块加工后拼接成整体实心结构。
3.一种轻质高强度耐高温腹鳍成型方法，通过将加工后的前连接头和后连接头嵌套到夹芯上，在外表面铺层碳布后将产品放入模具中注塑树脂高温固化成型，具体包括：
(a)夹芯加工:用PMI泡沫加工成整体实心结构；
(b)前连接头和后连接头机械加工成型；
(c)前连接头和后连接头与夹芯嵌套组合通过树脂胶结成结构单元；
(d)在前连接头、后连接头和夹芯界面层之间粘接胶膜层；
(e)在夹芯前缘铺层玻璃布，玻璃布浸渍双马树脂；
(f)在外表面铺层碳布后将产品放入模具中注塑树脂高温固化成型。
4.根据权利要求3所述的一种轻质高强度耐高温腹鳍成型方法，其特征在于在所述腹鳍采用树脂传递模塑成型(RTM)工艺整体制备。
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CN102848622A (zh) * 2012-09-06 2013-01-02 江苏兆鋆新材料科技有限公司 一种具有pmi泡沫芯材的夹芯材料及其制备方法
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CN105416567A (zh) * 2015-11-13 2016-03-23 中国人民解放军国防科学技术大学 一种蒙皮、无人机机翼及制备方法、尾翼及制备方法

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