固体火箭发动机 HTPB推进剂燃速性能老化研究

Research on Burning Rate Properties of HTPB Propellant in the Solid Rocket Motor

摘要:

为研究某型固体火箭发动机高燃速端羟基聚丁二烯(HTPB)推进剂在全寿命期内的燃烧性能——燃速,通过高温加速老化实验和活化能理论推测出发动机推进剂在常温 25℃下和高温 70℃下的老化速度；由此,通过高温 70℃的加速老化实验来获得不同贮存期的发动机推进剂试验样本；通过推进剂燃烧实验,测试了不同贮存期的推进剂的燃速,结果表明,随着发动机贮存时间的延长,HTPB推进剂燃速逐渐降低。

Abstract:

The aging velocity of motor propellant at the environment temperature 25°C and high temperature 70°C was pre.dicted by the accelerated aging test and activation energy theory in order to study the burning properties of solid-rocket-motor HTPB propellant during the full service life. By the accelerated aging test at the high temperature 70°C, the experi.mental specimens were gained as the specimens of motor propellant with different storing years. The burning rate was test.ed by burning test of propellant specimens with different storing years. The testing results showed that the burning rate ofpropellant increasingly went down with motor service life increasing.