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

作　　者：尤文斌[1,2] 马铁华[1,2] 丁永红[1] 崔敏[1] 

机构地区：[1]中北大学电子测试技术重点实验室,太原030051 [2]中北大学计算机与控制工程学院,太原030051

出　　处：《固体火箭技术》2014年第2期267-271,共5页Journal of Solid Rocket Technology

基　　金：国防科技点实验室基金(9140C120409);山西省青年科技研究基金(2013021015)

摘　　要：利用抗恶劣环境的存储测试技术,设计了一种火箭分离端面瞬态压力记录系统。对压力传感器采用的隔热处理进行了理论分析、ANSYS数值仿真和实验测试,结果表明在传压管道中填充硅脂可对1 s以内的瞬态高温起到较好的隔热效果。通过激波管校准实验获得系统固有频率达到56 kHz,动态误差小于5%,在火箭分离实验中成功记录了分离时一级火箭端面的压力信号。通过仿真及实测证明了该系统具有良好的实用性和可靠性。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 ls.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 

分 类 号：V441[航空宇航科学与技术—飞行器设计]