全封闭中空异型薄壁复合材料结构成型

Structural Molding of Fully Enclosed Hollow Special-shaped Thin-walled Composite Materials

以某航天器复合材料一体化摇臂为实例,针对其全封闭、非线性、变截面、变壁厚、细长中空的薄壁结构进行成型工艺方案研究。通过以可溶性芯模为铺层芯模,解决了铺层和脱模问题;选用气囊加压方式,解决了加压和成型问题。结果表明:经过4次-65~60℃的高低温循环试验,摇臂结构内部无分层、裂纹等缺陷产生;制备的复合材料摇臂顺利通过鉴定级力学试验,力学性能满足设计要求。采用气囊加压和可溶性芯模相结合的工艺方案,实现了低成本、短周期制备航天器复合材料主承力构件的目标,对类似的全封闭异型复合材料结构的研制具有一定借鉴意义。

Taking a spacecraft composite material integrated rocker arm as an example,the molding process plan is studied for its fully enclosed,nonlinear,variable cross-section,variable wall thickness and slender hollow thin-walled structure.By using the soluble mandrel as the layering mandrel,the problems of layering and demoulding are solved.The airbag pressurizing method is selected to solve the problems of pressurizing and forming.The results show that after 4 high and low temperature cycle tests between-65℃ and 60℃,there are no defects such as delamination or cracks in the rocker structure.The prepared composite rocker successfully passes the appraisal level mechanical test,and the mechanical properties meet the design requirements.The combination of airbag pressurization and soluble mandrel technology has achieved the goal of low-cost and short-period preparation of the main bearing components of spacecraft composite materials,which has certain reference significance for the development of similar fully enclosed special-shaped composite material structures.