Flexseal Nozzle Thermal Protection Characterization

摘要：

This paper is concerned with the thermal protection characteristics of the flexseal nozzle in solid rocket motors. The thermal protection system considered includes the flexible joint insulation boot and the compound-structure nozzle. The pyrolysis/char process of the joint insulation boot was simulated. The transient in-depth thermal response and surface recession of the nozzle assembly were predicted. Results show that the flexible joint thermal protection is easy to realize because a flow stagnant zone forms near the flexible joint, leading to low temperature and weak heat transfer. The thermal protection of the nozzle housing is effective for limited char depth of charring ablators and small erosion rate of carbon-carbon throat.

作者: ZHANG Xiaoguang LIU Yu REN Junxue ZHAN Kai

作者单位: Faculty 403, School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100 School of Engineering Applied Science, The George Washington University, Washington, DC 20052, USA

会议类型: 国际会议

会议名称: 2011 International Autumn Seminar on Propellants,Explosives and Pyrotechnics(2011国际推进剂、炸药、烟火技术秋季研讨会)

会议地点: 南京

会议语种:英文

页码: 709-713

在线出版日期: 2011-09-20（万方平台首次上网日期，不代表论文的发表时间）