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Date of Publication:2022-10-06

Journal:装备环境工程

Volume:15

Issue:2

Page Number:1-7

ISSN No.:1672-9242

Abstract:Objective To study the evolution performance and damage mechanism of carbon fibers/bismaleimide (CF/BMI) composites used as structure materials in spacecrafts and provide basis for forecasting and assessing its service performance and life in space environment used on its broad application. Methods Ground facilities were used to simulate different space envi-ronment factors involving vacuum thermal cycling, proton and electron irradiation. Properties and corresponding damage mechanisms of CF/BMI composite in space environment were investigated by dynamic mechanical analysis (DMA), thermal gravimetric analysis (TGA), X-ray photoelectron spectroscopy (XPS), thermal expansion analysis, atomic force microscopy (AFM) and mechanical tests, respectively. Results Vacuum thermal cycling could induce matrix outgassing and interfacial debonding, which resulted in the reduction in the transverse tensile strength. While the flexural strength and ILSS increased firstly and then fell back to a plateau value, which were affected by a crosslinking effect in the early stage. Proton radiation could cause molecular bond breakage in surface layer of the composites, thereby leading degradation of thermal and mechanical performance. Electron radiation could introduce both degradation and cross-linking effect in the irradiation process, while the degradation effect played a dominant role at higher fluences and thus became a decisive factor for degradation of thermal and mechanical performance. Conclusion The expected results would provide a useful theoretical foundation for assessing and forecasting the service performance and service life of CF/BMI composites applied in space environment.

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