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以芳纶纤维/环氧树脂(F-3A/EP)缠绕层作为固体火箭发动机用复合材料壳体、三元乙丙橡胶(EPDM)作为绝热层,采用适宜的胶粘剂制备壳体/EPDM、Φ480 mm壳体/EPDM和大尺寸壳体/EPDM胶接件,并着重探讨了固化条件(温度、时间等)对上述胶接件界面拉伸强度、剪切强度和剥离强度等影响。研究结果表明:3种类型的试样经130℃固化6 h后,其界面拉伸强度(3.02 MPa)、剪切强度(5.42 MPa)均明显提高,而Φ480 mm壳体/EPDM和大尺寸壳体/EPDM胶接件的剥离强度均达到5.84 N/mm,说明该胶粘剂及固化工艺完全满足壳体对EPDM绝热层的界面粘接要求;继续提高固化温度或延长固化时间,并不能显著提高胶接件的剥离强度,但对胶接件的成型工艺要求明显提高。
Aramid fiber / epoxy resin (F-3A / EP) winding layer as a solid rocket motor composite shell, EPDM as a thermal insulation layer, the use of suitable adhesive preparation shell / EPDM, Φ480 mm shell / EPDM and large-size shell / EPDM adhesive. The effects of curing conditions (temperature, time, etc.) on the tensile strength, shear strength and peel strength of the interface were emphasized. The results show that the interfacial tensile strength (3.02 MPa) and shear strength (5.42 MPa) of the three types of samples are obviously increased after curing at 130 ℃ for 6 h, while the Φ480 mm shell / EPDM and large size shell PE / EPDM adhesive peel strength reached 5.84 N / mm, indicating that the adhesive and curing process to fully meet the EPDM insulation shell shell interface bonding requirements; continue to increase the curing temperature or extend the curing time, and can not significantly improve the plastic Peel strength of the connector, but the plastic molding process requirements significantly improved.