Coupled fluid-structure 3-D solid rocket motor simulations

Abstract

We describe our numerical method for threedimensional simulations of solid rocket motors in which the internal gas dynamics, the combustion of the propellant, and the structural response are fully coupled. The combustion zone is treated as a thin layer using appropriate jump conditions, and the regression rate is determined using a nonlinear dynamic combustion model. An Arbitrary Lagrangian-Eulerian formulation is used in the gas dynamics and structural mechanics modules to follow the regression of the propellant. We demonstrate the parallel scalability of our ALE implementation and its ability to handle significant burn back of the propellant on a model problem with a very high burn rate.

固体火箭发动机点火瞬间流固耦合综述

“…2000 年美 国伊利诺斯大学先进火箭仿真中心(CSAR)建立了 RSRM 固体火箭发动机的三维流固耦合模拟方法, 采用并行代码, 并研制开发了点火瞬态过程仿真软 件 GEN1 [18] . 该软件采用欧拉预估校正算法, Arbitrary [19] . 从结构示意图(图 2)来看, 新版软 件共分为物理模块(Rocflo, Rocburn, Rocsolid)、基础 模块(Rocface, Rocpanda)和驱动模块(Driver)三部分.…”

Some Recent Developments in Rocket Core Dynamics

“…Such computational capabilities are currently under development by a number of dedicated scientists, including Dick, Heath, Balachandar, Moser, Fiedler, Najjar and others at the Center for Simulation of Advanced Rockets. [50][51][52][53] There is no doubt that the efforts expended by this body of scientists stand to provide the best diagnostic and predictive tools in the history of rocket development. However, their efforts are not without challenges either.…”

Burning surfaces evolution in solid propellants: A numerical model

“…The first published methods for either quasi-static, e.g. [2,3] or dynamic [4][5][6], coupling between gas and solid require interfaces with interpolation techniques as well as separate flow solvers and mesh generators for each phase. The latter poses particular demands on the designer, especially in three dimensions, where generation of geometrically complex (e.g.…”