固体火箭发动机喷管喉径瞬变值的计算和预示

介绍了由固体火箭发动机试验后实测数据计算喷管喉径瞬变值的方法.该方法是在引入化学无量纲烧蚀率概念,并应用一维热传导方程解出喉径表面温度下提出的.该法预示结果与实测结果比较表明,相对误差不超过0.52%,而且方法简单,便于工程应用.

The Calculation and Prediction of Transient Value of Nozzle Throat Radius

A method of calculating the transient value of nozzle throat radius from actualmeasured data after solid rocket motor firing is presented.The method is based on intro-ducing a concept of thermochemical dimensionless ablation rate and using 1-D hcat con-duction equation to solve surface temperature of the throat.Comparison of the predictedresults by the method with the actual measured data shows that the method is simple andcould be conveniently applied to engineering with a relative error of less than 0.52%.