STTR Phase I: Multi-Dimensional Hydrodynamic Stability Analysis Tool for Solid Rocket Motors

这项小型企业技术转让（STTR）第一阶段项目旨在确定为火箭、燃气轮机和大型发动机开发流体动力燃烧稳定性分析设计工具的可行性。由于燃烧室在较低的混合比下运行以避免NOx污染问题，涡流液体火箭发动机被设计为涡流流来冷却发动机，固体火箭发动机被设计为更长的L/D比，因此与旋转流相关的燃烧稳定性问题变得非常重要。在这项工作中，分析模型适用于简单的几何将转移到一个通用的三维能力的稳定工具。对于这一最初的努力，重点是为固体火箭发动机工业开发一种流体动力稳定性工具。目前，许多大型固体火箭发动机都存在流体动力稳定性问题，包括航天飞机RSRM、泰坦和阿丽亚娜5号。通过避免设计过程中的稳定性问题，该工具不仅有可能节省收入和动力损失，而且还可以防止开发项目因后期设计问题而取消。

This Small Business Technology Transfer (STTR) Phase I project is to determine the feasibility of developing a hydrodynamic combustion stability analysis design tool for rockets, gas turbines, and large engines. As combustors are run at leaner mixture ratios to avoid NOx pollutant issues, vortex liquid rocket engines are designed with swirling flows to cool engines, and solid rocket motors are built with longer L/D ratios, combustion stability issues associated with rotating flows become significant concerns. In this work analytic models applied to simple geometries will be transferred into a general 3D capable stability tool. For this initial endeavor, the focus is on developing a hydrodynamic stability tool for the solid rocket motor industry. Currently, many large solid rocket motors exhibit hydrodynamic stability problems, including the Shuttle RSRM, Titan, and the Ariane V. By avoiding stability issues in the design process, this tool has the potential to not only save on revenue and loss in momentum, but also prevent developmental programs from being cancelled due to design problems late in the process.