Strength criterion of composite solid propellants under dynamic loading

作     者：Zhe-jun Wang Hong-fu Qiang Guang Wang Biao Geng 

作者机构：206Staff Room Xi'an Hi-Tech Institute 

出 版 物：《Defence Technology（防务技术）》 (Defence Technology)

年 卷 期：2018年第14卷第5期

页      面：457-462页

核心收录：

学科分类：08[工学] 0806[工学-冶金工程] 0817[工学-化学工程与技术] 0826[工学-兵器科学与技术] 0805[工学-材料科学与工程（可授工学、理学学位）] 0802[工学-机械工程] 0703[理学-化学] 0701[理学-数学] 0801[工学-力学（可授工学、理学学位）] 0702[理学-物理学] 

基　　金：financial support of the National 973 Program in China (No. 61338) the National Funds in China (Nos.11772352, 61407200203 and 51328050101) 

主　　题：Strength criterion Unified strength theory Composite solid propellant Dynamic loading Biaxial tension 

摘      要：Based on the dynamic loading(1-100 s^(-1)) experiments under different temperatures(223-298 K) and stress states, uniaxial and biaxial strength criterion of a Hydroxyl-terminated polybutadiene(HTPB)based composite solid propellant were further investigated. These experiments were conducted through the use of a new uniaxial INSTRON testing machine, different new designed gripping apparatus and samples with different configurations. According to the test results, dynamic uniaxial tensile strength criterion of the propellant was directly constructed with the master curve of the uniaxial maximum tensile stress. Whereas, a new method was proposed to determine the dynamic uniaxial compressive strength of the propellant in this study. Then uniaxial compressive strength criterion of the propellant was constructed based on the related master curve. Moreover, it found that the uniaxial tensilecompressive strength ratio of the propellant is more sensitive to loading temperature under the test conditions. The value of this parameter is about 0.4 at room temperature, and it reduces to 0.2-0.3 at low temperatures. Finally, the theoretical biaxial strength criterion of HTPB propellant under dynamic loading was constructed with the unified strength theory, the uniaxial strength and the typical biaxial tensile strength. In addition, the theoretical limit lines of the principal stress plane for the propellant under dynamic loading at different temperatures were further plotted, and the scope of the limit line increases with decreasing temperature.