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根据固体火箭发动机喉部结构的实际工况,取样并设计试验,采用SRV高温摩擦磨损试验机测试了碳/碳与模压石棉/酚醛材料间的热摩擦系数,总结了这两类材料间的摩擦系数随温度、接触载荷及摩擦速度的变化规律。试验结果表明,碳/碳与模压石棉/酚醛材料间的热摩擦系数随温度升高呈非线性单调下降趋势;含胶层的两材料组件间摩擦系数明显高于无胶层组件间摩擦系数;温度一定条件下,载荷增加使得摩擦系数小幅降低;随着摩擦速度的提高,摩擦系数呈增大趋势。
According to the actual conditions of the solid rocket engine throat structure, the sampling and design of the test, the use of SRV high temperature friction and wear testing machine carbon / carbon and molded asbestos / phenolic material between the thermal friction coefficient, summarizes the friction between these two types of materials Coefficient changes with temperature, contact load and friction velocity. The results show that the coefficient of thermal friction between carbon / carbon and asbestos / phenolic composites decreases monotonically with the increase of temperature. The friction coefficient between the two materials with adhesive layer is obviously higher than the friction coefficient with no glue layer. Under the conditions, the friction coefficient decreases slightly due to the increase of the load. As the friction speed increases, the friction coefficient increases.