摘要
中型固定翼无人机机翼梁为碳纤维复合材料层压结构,传统的阴模-预浸料成型虽然能极大提高外形尺寸稳定性,但该方法即使在引入硅橡胶芯模也较难以确保圆角处的正压力以及因其成型带来的架桥、气泡裹入等现象;本文利用组合式自适应均压板辅助工装及阳模-预浸料成型方法,在确保机翼梁制件外表面质量的同时不仅显著提高了机翼梁制件内表面质量,还使得工艺得到明显简化,极大地避免了因成型带来的架桥、气泡裹入等现象;并通过随炉件制作及性能测试得到单向预浸料的弯曲强度为1549 MPa,弯曲模量为110 GPa,层间剪切强度为87 MPa。
The wing beam of medium fixed-wing unmanned aerial vehicle was a carbon fiber composite laminated structure.Although the conventional female mold-prepreg molding method could greatly improve the dimensional stability of the shape,it is difficult to ensure the positive pressure at the rounded corners and the phenomenon of bridging and bubble wrapping due to its forming even when the silicon rubber core mold was introduced.In this paper,the combined adaptive equalizing plate auxiliary tooling and the male mold-prepreg forming method were used to ensure the outer surface quality of the wing beam parts,and not only improve the inner surface quality of the wing beam parts significantly,but also simplify the process obviously,which greatly avoids the phenomenon of bridging and bubble wrapping caused by the forming.Through the furnace production and performance test,the bending strength,bending modulus and interlaminar shear strength of unidirectional prepreg are 1549 MPa,110 GPa and 87 MPa,respectively.
作者
张旭东
赵伟超
张娟
ZHANG Xudong;ZHAO Weichao;ZHANG Juan(Institute of 365,Northwestern Polytechnic University,Xi’an 710065;Xi’an Aviation Brake Technology Co.,Ltd.,Xi’an 710065)
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2022年第1期94-97,共4页
Aerospace Materials & Technology
关键词
环氧预浸料
中温固化
复合材料成型
机翼梁
Epoxy prepreg
Mid-temperature curing
Composite molding
Wing spar
