摘要
本文介绍了一种复合材料卫星整流罩端头的浸胶、铺层、固化工艺。研究表明,大尺寸、变厚度复合材料端头采用阴模铺层和热压罐固化工艺,成型后的产品外表面平整、光滑、无皱折,不仅满足了气动加热表面的质量要求,力学性能也满足了设计要求。
One forming process of a composite fairing nose includingadhesive infiltration, lamination, curing is introduced. The experimentalresults show that when the large fairing nose with different thicknessis laminated in forming matrix and cured in autoclave, its surface issmooth which is satisf actory to the surface quality of pneumatic heatingmode, and the mechanical property of the structure meets the designspecification.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
1993年第6期33-36,共4页
Aerospace Materials & Technology
