复合固体推进剂拉伸/压缩性能对比研究(英文)  

Comparative Research of Tensile and Compressive Modulus of Composite Solid Propellant for Solid Rocket Motor

作　　者：任萍[1] 侯晓[2] 何高让[2] 郜婕[2] 何铁山[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]中国航天科技集团公司第四研究院第四十一所固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安710025

出　　处：《宇航学报》2010年第10期2354-2359,共6页Journal of Astronautics

摘　　要：为了获得药柱受压状态的模量参数,开展了推进剂压缩性能的探索测试。参照拉伸标准试件,进行了压缩试件尺寸的设计与调试,通过不同高度试件的测试结果及破坏形貌分析,确定了试件尺寸。在此基础上进行了不同应变下的推进剂拉/压对比测试。相同应变率下,压缩模量较拉伸模量高,压缩模量随压缩速度的变化规律与拉伸模量一致,随着速度的提高,模量随之提高。In order to get the modulus of composite solid propellant under compression state,compression tests are carried out. The specimen is designed for compression tests with reference to the standard tensile specimen. Through analysis of a lot of test results and failure modes to different specimen,the size of specimen is determined. Based on the determined dimension,comparative test of tension and compression are performed under different strain rates. Compressive modulus are higher than tensile modulus at the same strain rate. The varying law of compressive modulus with compressive speed is consistent with tensile modulus. As the speed increases the velocity,the modulus becomes higher.

关 键 词：推进剂 拉伸 压缩 初始模量 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]