摘要
对蜂窝侧向变形机理的研究现状进行了综述,对Nomex蜂窝在180℃下的强度性能进行了测试,并在此基础上建立了蜂窝侧向变形的力学模型。分析表明,常规蜂窝夹层结构采用热压罐共固化时不产生蜂窝侧向变形的条件是倾角不大于25°,织物预浸料边缘有牢靠的拴系,蜂窝高度不宜过大。预浸料边缘采用防滑带拴系和提高蜂窝的侧向刚度是解决蜂窝侧向变形的关键,其中提高蜂窝侧向刚度的方法包括胶膜法、隔膜法和预固化织物法等工艺方法。相关工艺试验表明:对于高度60mm、倾角30°的常规密度蜂窝夹层结构,胶膜法效果不佳,隔膜法和预固化法是消除高蜂窝夹层结构侧向变形的有效措施,预固化法比隔膜法具有重量优势。
The research status of honeycomb lateral crush mechanism was summarized,and the strength of Nomex honeycomb at 180℃was tested.On this basis,the mechanical model of honeycomb lateral crush mechanism was established.The analysis shows that:when the conventional honeycomb sandwich structure adopts cocure process,the condition of no honeycomb lateral crush problems is that the inclination angle is no more than 25°,the edge of the fabric prepreg is firmly tied-down,and the honeycomb height should not be too high.The key to solve the honeycomb lateral crush problem is to adopt friction belt to tie-down the edge of prepreg and improve the lateral rigidity of honeycomb.The methods to improve the lateral rigidity of honeycomb including adhesive film method,septum method and pre-curing fabric method.The processing test result shows that:for the conventional honeycomb sandwich structure with a height of 60mm and an inclination angle of 30°,the stabilization effect of adhesive film method is not good,the septum method and precuring fabric method are effective measures to solve lateral crush problem of honeycomb sandwich structure,and the precuring fabric method has the weight advantage over the septum method.
作者
郝新超
胡杰
HAO Xinchao;HU Jie(COMAC Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)
出处
《航空制造技术》
2020年第13期69-74,82,共7页
Aeronautical Manufacturing Technology
关键词
复合材料
蜂窝
芯材变形
共固化
蜂窝夹层结构
Composites
Honeycomb
Core crush
Cocure process
Honeycomb sandwich structure
