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

该小型企业技术转让（STTR）第一阶段项目旨在确定开发用于火箭、燃气轮机和大型发动机的流体动力燃烧稳定性分析设计工具的可行性。由于燃烧室以更稀的混合比运行以避免NOx污染物问题，涡流液体火箭发动机设计有旋流以冷却发动机，并且固体火箭发动机建造有更长的L/D比，因此与旋转流相关的燃烧稳定性问题成为重要的问题。在这项工作中，适用于简单几何形状的分析模型将被转移到一个通用的3D稳定性工具。对于这一初步的奋进，重点是发展固体火箭发动机工业的流体动力稳定性工具。目前，许多大型固体火箭发动机表现出流体动力学稳定性问题，包括航天飞机RSRM，泰坦和阿丽亚娜V通过避免稳定性问题在设计过程中，这个工具有可能不仅节省收入和损失的势头，但也防止开发计划被取消，由于设计问题的后期过程。

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.