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在固体火箭发动机的研制中,为了确定固体推进剂的破坏标准,有必要研究其破坏过程。从这种观点出发,本文把破坏过程作为一个研究课题。我们选用了含有细颗粒填料的大推力可控型固体火箭发动机用CTPB(端羧基聚丁二烯)系复合固体推进剂。通过多次反复拉伸试验,弄清了它的应力-应变特性、破坏能等力学性质。实验结果表明:不仅对固体推进剂的破坏过程有了新的认识,而且在预测试验用推进剂的物性、强度方面也得到实际应用。
In the development of solid rocket motor, in order to determine the destruction of solid propellant standards, it is necessary to study the destruction process. From this point of view, this article takes the process of destruction as a research topic. We chose CTPB (Carboxypolybutadiene) based composite solid propellants for high thrust controllable solid rocket motors containing fine particulate fillers. Through several repeated tensile tests, it has been clarified its mechanical properties such as stress-strain characteristics and failure energy. The experimental results show that it not only has a new understanding of the destruction process of solid propellants, but also has practical application in predicting the physical properties and strength of test propellants.