热循环和紫外线辐射对碳纤维/双马来酰亚胺聚合物复合壳稳定性影响的实验研究

Experimental Study on the Effects of Thermal Cycling and Ultraviolet Irradiation on Stable Characteristics of Carbon Fiber/Bismaleimide Polymer Composite Shells.

作者信息

Zhang Zheng, Ji Xinyue, Sun Min, Xiong Libin, Zhang Guang, Ding Wenjie, Li Jiquan, Jiang Shaofei

机构信息

College of Mechanical Engineering, Zhejiang University of Technology, Hangzhou 310023, China.

Key Laboratory of Special Purpose Equipment and Advanced Processing Technology, Ministry of Education and Zhejiang Province, Zhejiang University of Technology, Hangzhou 310023, China.

出版信息

Materials (Basel). 2025 Apr 24;18(9):1942. doi: 10.3390/ma18091942.

DOI:10.3390/ma18091942

PMID:40363447

原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC12072402/

Abstract

Carbon fiber/epoxy composites are widely used in aerospace due to their strength and ease of fab weatherrication, but they suffer from glass transition at high temperatures. In contrast, carbon fiber/bismaleimide composites exhibit superior thermal stability, irradiation resistance, and toughness. This study investigates the effects of thermal cycling and UV irradiation on carbon fiber/bismaleimide composite shells. Anti-symmetric shells with varying ply angles were tested under two-point tensile loading. Results show that these shells maintain stability between -70 °C and 180 °C, outperforming epoxy-based composites. This research offers valuable insights for aerospace applications of such bistable shells under thermal and UV aging conditions.

摘要

碳纤维/环氧树脂复合材料因其强度和易于制造的特点而在航空航天领域得到广泛应用，但它们在高温下会出现玻璃化转变。相比之下，碳纤维/双马来酰亚胺复合材料表现出卓越的热稳定性、抗辐照性和韧性。本研究调查了热循环和紫外线辐照对碳纤维/双马来酰亚胺复合壳的影响。在两点拉伸载荷下测试了具有不同铺层角度的反对称壳。结果表明，这些壳在-70°C至180°C之间保持稳定，性能优于环氧基复合材料。这项研究为这种双稳态壳在热老化和紫外线老化条件下的航空航天应用提供了有价值的见解。