CAJ | 학술논문

制备了分别以光滑层结构热解炭(SL)、树脂炭和粗糙层结构热解炭(RL)为基体的A, B和C 3种C/C复合材料，在M2000摩擦试验机上与具有SL炭基体的C/C复合材料配副进行环-块滑动摩擦。结果表明：随载荷增加，有SL基体的A材料或树脂炭基体的B材料的摩擦因数较低，随载荷增加摩擦因数呈下降趋势；有RL炭基体的C材料的摩擦因数先升高后轻微波动，在100 N时达到峰值0.145。当载荷大于80 N后，A和B材料的体积磨损稳定，数值接近，不大于0.39 mm3，而C材料的体积磨损随载荷增加先升高后降低，在100 N时最高达1.47 mm3。随时间延长，A材料的摩擦因数稳定速度最快，B和C材料的在5 h实验后仍有所下降。SEM形貌表明， A材料摩擦表面有大块摩擦膜剥落，B材料则有点状的粘着磨损；3种材料主要磨损机制为磨粒磨损。
제비료분별이광활층결구열해탄(SL)、수지탄화조조층결구열해탄(RL)위기체적A, B화C 3충C/C복합재료，재M2000마찰시험궤상여구유SL탄기체적C/C복합재료배부진행배-괴활동마찰。결과표명：수재하증가，유SL기체적A재료혹수지탄기체적B재료적마찰인수교저，수재하증가마찰인수정하강추세；유RL탄기체적C재료적마찰인수선승고후경미파동，재100 N시체도봉치0.145。당재하대우80 N후，A화B재료적체적마손은정，수치접근，불대우0.39 mm3，이C재료적체적마손수재하증가선승고후강저，재100 N시최고체1.47 mm3。수시간연장，A재료적마찰인수은정속도최쾌，B화C재료적재5 h실험후잉유소하강。SEM형모표명， A재료마찰표면유대괴마찰막박락，B재료칙유점상적점착마손；3충재료주요마손궤제위마립마손。
Three kinds of C/C composites with different matrix carbon were prepared, and then the ring-block sliding friction behavior was tested on M2000 tester against C/C ring with smooth lamination structure pyrocarbon matrix (SL). The results show that the coefficient of friction (COF) of the composite with SL (composite A) or resin carbon matrix (composite B) is lower than that of the composite with rough lamination structure pyrocarbon matrix (composite C). The COF of composite A and B decreases with the increase of load, while that of composite C increases at first and then decreases with the highest value of 0.145 at 100 N. The volume loss of composite A and B is close and remain stable when the load is higher than 80 N with the highest value is only 0.39 mm3. But the value loss of composite C increases up to the highest value of 1.47 mm3 at 100 N and then remains some fluctuation. The COF of composite A can reach the stable value quickly while those of composite B and C still decrease after 5 hours’ test. SEM images of worn surface show that some large film on composite A is peeled off, some dotted adhesive wear scar can be found on the worn surface of composite B. Abrasive worn is the main wear mechanism for tribological behavior of the three C/C composites.