摘要
修正了固液混合火箭的固体燃料燃面退移速率预示模型中对流换热和汽化热的计算,将其用于固体燃料冲压发动机中,考虑了固体燃料冲压发动机中来流空气总温及装药长度的影响。编写了固体燃料冲压发动机燃面退移速率预示程序。计算结果表明,当来流空气总温大于450 K时,计算误差的平均值不超过6.55%,所完善的模型的计算结果与试验值吻合很好,该模型能准确预示固体燃料冲压发动机中燃面退移速率;燃面退移速率与装药长度的-0.23次方成正比。
The calculation error of convection heat transfer and heat of vaporization of hybrid rocket propellant regression rate model was corrected.Then,it was used to predict propellant regression rate of solid fuel ramjet.The effects of air total temperature in solid fuel ramjet and length of solid propellant also were considered.The predicting program of propellant regression rate in solid fuel ramjet was obtained.The calculating results show that： when the total temperature of air was greater than 450 K,the average value of errors was lower than 6.55%,the modified model results agree well with the experimental data.The model can accurately predict propellant regression rate of solid fuel ramjet;the propellant regression rate is proportional to-0.23 power of the length of propellant.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第5期613-618,共6页
Journal of Solid Rocket Technology
