摘要
研究了固体火箭发动机推力终止试验时，反向喷管堵盖打开时间及同步性测量方法。在测量中配置了抗干扰能力强、时间分辨率为微秒级的数字记录系统和多功能模拟记录系统，解决了时间测量中产生和获取起始脉冲及终止脉冲信号的关键技术，消除了引爆机构产生的冲击波和气体电离的影响。该测量方法经过多次充气容器冷试和发动机地面静止试验的考核，证实了测出的数据准确可靠，克服了时间测量数据分散度大的缺点。
Measuring method of opening time and operating synchronism of the reverse nozzle closures of solid rocket motor during thrust termination test was studied.The high anti interference digital recording system,which has μs magnitude time resolution,and multi function analog recording system was used.The method solves the key technique of generation and measurement of the initial pulses and termination pulses,and eliminates,the effects of the explosion wave and gas ionization from detonation system.It is proved that the method is accurate and reliable by some cold flow tests and ground static tests,overcoming the data dispersity.
出处
《固体火箭技术》
EI
CAS
CSCD
1998年第4期68-72,共5页
Journal of Solid Rocket Technology
