The development of a multi-disciplinary CFD code and the application of the code to simulate Titan IV 7-segment solid rocket motor (SRM) transient flowfields, coupled with propellant deformation, are presented. The code consists of four modules and is modularized such that each module can be replaced or updated with the rest of the modules remaining intact. The four modules are: the flow solver, the structural analysis, the thermal analysis, and the grid generation modules. The flow solver module is the core of the code. The salient features of the flow solver are: (a) the boundaries can move in any arbitrary manner, and (b) the conservation principles are always satisfied since the movements of the boundaries and computational grids are incorporated in the equations of motion. Geometrically nonlinear theory of elasticity is used for the structural analysis module. Due to the interactive nature of the code, each simulation can be completed efficiently in a single job submission. Transient phenomena of ignition waves interacting with deformable propellant are presented. The effects of propellant deformation on the pressure distribution inside the motor are discussed.
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机译:介绍了多学科CFD代码的开发以及该代码在模拟Titan IV 7段固体火箭发动机(SRM)瞬态流场以及推进剂变形方面的应用。该代码由四个模块组成,并且经过模块化处理,因此可以在其余模块完好无损的情况下替换或更新每个模块。四个模块是:流量求解器,结构分析,热分析和网格生成模块。流程求解器模块是代码的核心。流量求解器的显着特征是:(a)边界可以以任意方式移动,并且(b)始终满足守恒原理,因为边界和计算网格的运动已包含在运动方程中。几何非线性弹性理论用于结构分析模块。由于代码具有交互性,因此可以在单个作业提交中高效地完成每个模拟。提出了点火波与可变形推进剂相互作用的瞬态现象。讨论了推进剂变形对电动机内部压力分布的影响。
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