固体火箭技术Issue(2)：267-271,5.DOI:10.7673/j.issn.1006-2793.2014.02.024
火箭分离端面压力测试技术研究及应用
Rocket separation face pressure testing technology research and application
摘要
Abstract
A transient pressure recording system was designed for rocket separation face transient pressure measurement. It uses storage testing technology to resist bad environment.The thermal insulation for pressure sensor was performed by theoretical analysis, ANSYS simulation and experiments,the results show the silicon grease filling in the pressure pipeline has good heat insulation effect for transient high temperature in 1s.The shock tube calibration experiment shows system inherent frequency is 56 kHz and dynamic error is less than 5%.The system successfully records the separation face pressure signal in rocket separation experiment.Simulation and test show that the system has good practicability and reliability.关键词
瞬态压力/隔热处理/记录仪/动态性能Key words
transient pressure/thermal insulation/recorder/dynamic performance分类
航空航天引用本文复制引用
尤文斌,马铁华,丁永红,崔敏..火箭分离端面压力测试技术研究及应用[J].固体火箭技术,2014,(2):267-271,5.基金项目
国防科技点实验室基金（9140C120409）；山西省青年科技研究基金（2013021015）。 （）
