摘要
以某大膨胀比的最大推力喷管为分析对象,研究其在分离状态下的气动响应性能。利用有限体积二阶迎风插值格式及SA湍流模型,结合二层增强型壁面函数,分析喷管内部的流动状态,详细讨论了该喷管流动中出现气流分离模态由自由激波(FSS)到受限激波(RSS)的变化情况。采用弱耦合CFD/CSD分析的方法,计算分离状态下喷管壁面瞬态的气动弹性响应。结果表明,在喷管起动过程中,随着内部压强的建立,喷管不同部分出现不同的结构变形。在瞬态起动阶段,喷管壳体未出现周期性振动变化。
A numerical study on high area ratio rocket engine is conducted to analyze the structural aeroelastic performance under the condition of flow separation. The finite volume method, the second order upwind scheme, SA turbulence model and enhanced wall function are employed to analyze the flow filed inside the rocket nozzle and discuss the transition of the separation pattern free shock separation （FSS） to restricted shock separation （RSS） in detail. An aeroelastic coupling procedure is performed with the loosely coupled CFD/CSD. The aeroelastic response of the nozzle during the condition of the flow separation were calculated. The simulation result reveals that periodic change in vibration doesn＇ t occur on the nozzle case during the startup transient.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第6期711-716,共6页
Journal of Solid Rocket Technology
基金
国家自然科学基金(51005179)
