中文摘要：

采用流固耦合数值模拟研究了液体火箭发动机高压供气系统中的电磁阀在地面试验中出现的不稳定现象.固体结构采用质量弹簧阻尼单自由度模型描述,纽马克算法（The Newmark Method）求解;流体控制方程为三维Euler方程,采用基于弹簧近似动网格的ALE（Arbitrary Lagrangian-Eulerian）有限体积格式求解.程序应用了新的离散几何守恒律和流固界面算法,采用“虚拟挡板通气”技术实现电磁阀开启过程引起的计算区域拓扑变化.验证算例表明程序的有效性及算法的精度.数值模拟复现了试验中出现的故障,认为故障机理是典型的颤振现象,指出电磁阀和减压器之间的管路长度是影响气体激振力频率的主要因素.

英文摘要：

The instability phenomena occurring in the ground test of the electromagnetic valve of the liquid rocket＇s high pressure feed system are studied in the fluid-structure interaction simulation. The solid structure is modeled by the mass- spring damper which only has one degree of freedom and is solved by the Newmark method. The fluid is governed by the three-dimensional Euler equation and is solved by the ALE （Arbitrary Lagrangian-Eulerian） finite volume schemewhich is based on the spring analogy dynamic mesh. The flow field solver employes a newly developed geometric conservation law and a new fluid-structure interface scheme. The flow field topology transition induced by the electromagnetic valve charging/ discharging is simulated by the virtual baffle technique. The effectiveness and accuracy of the proposed solver are verified by the verification example. The breakdown of the feed system which occurred during the ground test reappeared in the numeri- cal simulation, which is identified as the flutter phenomena of the feed system. We draw the conclusion that the key factor that influences the excitation force frequency of the gas flow is the pipeline length between the electromagnetic valve and the pressure regulator valve.