New discrimination method for ablative control mechanism in solid-propellant rocket nozzle

作     者：ZHANG Bin, LIU Yu, WANG ChangHui & REN JunXue School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China 

作者机构：School of Astronautics Beijing University of Aeronautics and Astronautics Beijing China 

出 版 物：《Science China(Technological Sciences)》 (中国科学（技术科学英文版）)

年 卷 期：2010年第53卷第10期

页      面：2718-2724页

核心收录：

学科分类：080703[工学-动力机械及工程] 082502[工学-航空宇航推进理论与工程] 08[工学] 0807[工学-动力工程及工程热物理] 0825[工学-航空宇航科学与技术] 

基　　金：supported by the National Hi-Tech Research and Development Program of China("863"Project)(Grant No.2008AA7020508) 

主　　题：nozzle Ablation diffusion control mechanism chemical kinetics control mechanism discrimination method 

摘      要：A reasonable discrimination method for ablative control mechanism in solid-propellant rocket nozzle can improve the calculation accuracy of ablation rate. Based on the different rate constants for reactions of C with H2O and CO2,a new discrimination method for ablative control mechanism,which comprehensively considers the influence of nozzle surface temperature and gas component concentration,is presented. Using this new discrimination method,calculations were performed to simulate the nozzle throat insert ablation. The numerical results showed that the calculated ablation rate,which was more close to the measured values,was less than the value calculated by diffusion control mechanisms or by double control mechanisms. And H2O was proved to be the most detrimental oxidizing species in nozzle ablation.