|
| Property Evolution and Damage Mechanism of CF/BMI Composite in Space Environment |
| Received:August 21, 2017 Revised:February 15, 2018 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/ issn.1672-9242.2018.02.001 |
| KeyWord:CF/BMI composite vacuum thermal cycling proton irradiation electron irradiation damage behaviors |
| Author | Institution |
| YU Qi |
Liaoning Key Laboratory of Advanced Polymer Matrix Composites & School of Aerospace Engineering, Shenyang Aerospace University, Shenyang , China |
| CHEN Ping |
State Key Laboratory of Fine Chemicals & School of Chemical Engineering, Institute of Chemical Engineering, Dalian University of Technology, Dalian , China |
| LU Chun |
Liaoning Key Laboratory of Advanced Polymer Matrix Composites & School of Aerospace Engineering, Shenyang Aerospace University, Shenyang , China |
| WANG Qi |
Liaoning Key Laboratory of Advanced Polymer Matrix Composites & School of Aerospace Engineering, Shenyang Aerospace University, Shenyang , China |
|
| Hits: |
| Download times: |
| 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 environment 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. |
| Close |
|
|
|