新一代大火箭底部热环境研究

Research on the Base Heating Environment of New Launch Vehicle

多喷管火箭底部热环境机理复杂、影响因素众多,历来是国内外新型火箭设计的难点和热点。新一代运载火箭采用全新动力系统,带来了更严酷的底部加热问题。为突破这一技术难题,从机理分析、飞行遥测反算、工程方法计算、搭载发动机试车热环境测量、搭载飞行遥测、热流考核试验、数值仿真计算等多个方面开展研究,辨识出关键要素,建立了底部热流曲线设计方法,为型号底部结构防热设计提供合理依据,推动了中国在多喷流干扰底部复杂热环境问题研究上的技术进步。

Multi-rocket plume induced base flow is highly complex due to various flow structures,flow regimes and large thermal and momentum gradients within the base region.These extreme environments make base flows challenging but also critical to assess and predict to prevent vehicle failure.The new vehicles adopts new propulsion systems.To accurately predict and understand the base heating,the launch vehicle base flow physics have been investigated and flow processes observed during past years.Semi-empirical engineering tools,computational fluid dynamics,radiometer measurements on ground tests of rocket engine,and many other aspects,have been used to further investigate base flows for new vehicle,promoting in predicting and understanding the base heating of multi-rocket plume on the technological progress.