某运载火箭三级贮箱滑行段热分析计算

为保证某火箭三级发动机二次启动的可靠性，在分析滑行段热环境的基础上，用I-DEAS TMG软件时三级贮箱内增压气体、推进剂、固壁进行气液固三相耦合热分析。建立了简化的有限元模型，并综合考虑高温喷管延伸裙、空间外热流、三级底部各部件的遮挡等因素，计算了滑行段期间不同太阳入射角工况下的温度变化。计算和分析结果表明，高温喷管的辐射是影响三级底部热环境的主要因素。该运载火箭三级各部位温度变化能满足发动机二次启动的要求。

Thermal Analysis of Launch Vehicle Third Class Container during Space Sliding Time

To ensure the working reliability of the third class rocket engine during the satellite emission, the thermal coupling analysis of pressurization gas, propellant and container wall was studied through I-DEAS TMG in this paper. The simplified finite module was founded. The temperature under different solar incidences during the sliding period was computed when the effect of high temperature rocket engine, space heatload and many sheltering components located at third class rocket bottom were considered. The computation and analysis results showed that the radiation of the high temperature nozzle was the major factor that affected the thermo environment of the third class bottom. The temperature of the various parts for the third class container in the launch vehicle met the requirement for the second start-up.