固体火箭推进剂过保温后力学性能试验研究  

Experimental Investigation on Mechanical Property of Solid Rocket Propellant After Over-incubation

作　　者：王鸿丽[1] 许进升[1] 陈雄[1] 周长省[1] WANG Hongli;XU Jinsheng;CHEN Xiong;ZHOU Changsheng(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学机械工程学院,江苏南京210094

出　　处：《弹道学报》2018年第1期51-54,共4页Journal of Ballistics

摘　　要：为了研究固体火箭推进剂过保温后的力学性能,在保温温度为50℃的条件下,对NEPE推进剂哑铃型试件进行了3个不同拉伸速率下10组保温时间下的拉伸试验。试验结果表明,与未保温的NEPE推进剂试件相比,保温之后NEPE推进剂的强度有一定的提高,延伸率出现明显的下降;NEPE推进剂试件的保温时间越长,抗拉强度越大;在保温时间相同的情况下,保温次数越多,抗拉强度越大;保温时间和保温次数对NEPE推进剂的延伸率没有影响。In order to study the mechanical properties of solid rocket propellant after over-incubation,the tensile tests of dumbbell-type specimen of nitrate ester plasticized polyether(NEPE)propellant under three different tensile-rates and ten groups of different incubation time were carried out,and the incubation temperature was 50℃.The results show that compared with NEPE propellant without incubation,the strength of NEPE propellant is improved,and the elongation of NEPE propellant decreases after incubation.The longer the incubation time,the greater the tensile strength of NEPE propellant specimen.Under the same incubation time,the more the times of incubations,the greater the tensile strength of NEPE propellant specimen.The incubation time and the times of incubations have no effect on the elongation of NEPE propellant.

关 键 词：固体火箭推进剂 过保温 保温时间 力学性能 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]