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少烟幼畜(Maverich)固体火箭发动机的结构使用寿命估计是以解剖发动机的推进剂性能数据为基础进行的。为了在两年的时间里模拟五年的使用寿命,这些发动机经历了实验室加速化学和力学老化。用经验老化模型来推测发动机推进剂的性能和药柱横截面上的性能梯度,建立了有限元计算机模型来计算这些性能梯度,并确定发动机安全裕度与时间的函数关系。根据分析,预计这种发动机的使用寿命在10年之上。
Structural life estimates of Maverich solid rocket motors are based on anatomical engine propellant performance data. In order to simulate a five-year service life in two years, these engines underwent lab-accelerated chemical and mechanical aging. Empirical aging models were used to infer the performance of engine propellants and the performance gradients across the grain cross section. Finite element computer models were established to calculate these performance gradients and determine the engine safety margin as a function of time. According to the analysis, the service life of this kind of engine is expected to be over 10 years.