分瓣金属模辅助缠绕工艺成型舱段缩比件
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摘要
以某型号复合材料舱段研制为背景,提出用分瓣金属模辅助缠绕工艺整体成型内网格加强筋圆柱壳复合材料构件。依据舱段结构特点,设计了缩比件,并用分瓣金属模成型了碳纤维复合材料缩比件。研究结果表明,分瓣金属模可以成型出外形完整、尺寸准确的缩比件,且成型的构件尺寸稳定性好、精度高,但劳动强度大。试验表明,分瓣金属模辅助缠绕工艺可以整体成型内网格加强筋圆柱壳复合材料构件。
In this paper,a splitting metal mold assisted winding process,which could be used for internal grid rib reinforced cylindrical shell composite structure,was developed due to the background of the development of a certain type of composite material cabin. A scaling prototype of carbon fiber composite material was designed and formed by splitting metal mold according to the structural features. The research results show that complete shape and accurate dimension of the scaling cabin can be obtained through the use of splitting metal mold with good dimensional stability and high precision,but high labor intensity. The issues are discussed in the paper. Experiment results show that the internal grid reinforced cylindrical shell composite structure can be integrally formed by the splitting metal mold assisted winding process. Ideas on the future research composite material cabin are proposed in the paper.
In this paper,a splitting metal mold assisted winding process,which could be used for internal grid rib reinforced cylindrical shell composite structure,was developed due to the background of the development of a certain type of composite material cabin. A scaling prototype of carbon fiber composite material was designed and formed by splitting metal mold according to the structural features. The research results show that complete shape and accurate dimension of the scaling cabin can be obtained through the use of splitting metal mold with good dimensional stability and high precision,but high labor intensity. The issues are discussed in the paper. Experiment results show that the internal grid reinforced cylindrical shell composite structure can be integrally formed by the splitting metal mold assisted winding process. Ideas on the future research composite material cabin are proposed in the paper.
引文
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[13]郝卫,孙宏杰,蒋文革,等.蒙皮-网格-桁条结构复合材料共固化成型研究[C]//复合材料:创新与可持续发展(上册). 2010:10.
[14]提亚峰,董波,郭永辉,等. C/E复合材料网格缠绕结构三维建模与模具设计[J].宇航材料工艺,2010(4):23-26.
[2]Buragohain M,Velmurugan R. Study of filament wound grid-stiffened composite cylindrical structures[J]. Composite Structures,2011,93:1031-1038.
[3] Kruckenberg T,Paton R.航空航天复合材料结构件树脂传递模塑成型技术[M].李宏运,译.北京:航天工业出版社,2009.
[4]谢霞,邱冠雄,姜亚明.纤维缠绕技术的发展及研究现状[J].天津工业大学学报,2004,23(6):19-22.
[5]陈小平,杨杰,刘建超.复合材料网格结构的研究现状[J].宇航材料工艺,2009(2):6-11.
[6]刘雄亚,谢怀勤.复合材料工艺及设备[M].武汉:武汉工业大学出版社,1997.
[7]欧国荣,倪礼忠.复合材料工艺与设备[M].上海:华东化工学院出版社,1991.
[8]党旭佞,李煊,蒋元兴,等.碳纤维增强树脂基复合材料网格结构件成型模具及成型方法[J].专利库,2009.
[9]刘钧,尹昌平,曾竟成.软模辅助RTM制备舱段缩比件[J].玻璃钢/复合材料,2006(1):45-47.
[10]邓杰,刘建超. 4种网格结构模具用硅橡胶性能研究[J].粘接,2010(1):41-44.
[11]刘艳.一体化成型纤维缠绕网格承力筒模具设计[J].航空制造技术,2010(17):101-103.
[12]王维,苏峰,李晓丹,等.小端外翻法兰复合材料锥壳的模具设计[J].纤维复合材料,2009(2):40-42.
[13]郝卫,孙宏杰,蒋文革,等.蒙皮-网格-桁条结构复合材料共固化成型研究[C]//复合材料:创新与可持续发展(上册). 2010:10.
[14]提亚峰,董波,郭永辉,等. C/E复合材料网格缠绕结构三维建模与模具设计[J].宇航材料工艺,2010(4):23-26.