固体火箭发动机内绝热层烧蚀质量损失计算

Calculation of internal insulation ablation mass loss of solid rocket motor

运用较完备的烧蚀模型,采用了动边界显式差分格式,对固体火箭发动机内绝热层的烧蚀及其温度场进行了耦合计算。计算得到烧蚀率、炭化率、烧蚀厚度和炭化厚度,以及根据绝热层的工作时间计算出内绝热层的质量损失及发动机工作完成后一段时间内后效炭化质量损失。采用该方法不仅能使内绝热层设计更为合理,而且为后效推力的研究打下了基础。

Ablation and temperature field of a solid rocket motor were coupling calculated by the moving boundary show-difference method and the more perfect ablation model. Ablation rates, charring rates and thickness of ablation and charring were calculated. According to ablation time of the internal insulation, the internal insulation mass loss was calculated; the after-charring mass loss in the span after the motor work ended was also calculated. The method can be used to make the internal insulation design more reasonable , and it lays the foundations of after-thrust study .