摘要
高温燃气阀是固体飞行器姿轨控动力系统的重要控制装置。基于国内外燃气阀的研究,引入了静摩擦力和库伦摩擦力模型,设计一种浮动提升式燃气阀,采用动网格和UDF技术建立了燃气阀启闭过程中二维瞬态数值模型。计算结果表明,与普通喷管相比,该燃气阀内的流场不均匀性增加,阀门启闭过程中燃气阀及喷管内的流场变化是相近的,分析了在阀门启闭过程中不同开度下阀门流场内的亚音速回流区、流动分离以及激波分布情况,真实有效地模拟了燃气阀的启闭动态特性。仿真结果表明,该燃气阀结构合理,且可行性高。
High temperature gas valve plays an important role in the divert and attitude system of solid aerocraft. A 2-D un-steady simulation, based on the research of gas valve at home and abroad and the static force and coulomb friction model, was de-signed using dynamic grid and UDF technology to investigate the process of open-closed of gas valve. Calculation results show that the non-uniformity of gas valve is increasing compared with that of normal nozzle, and the change is similar in open-closed gas valve and nozzle flow field. The subsonic backflow area, flow separation and the distribution of the oblique shock wave in the valve flow field were analyzed under different openings during the open-closed process, and the simulation is real and effective for the open-closed characteristics of gas valve. The simulation results show that the valve structure is reasonable and feasible.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2015年第2期225-231,250,共8页
Journal of Solid Rocket Technology
基金
"十一五"民用航天科研预先研究项目
关键词
固体姿轨控系统
燃气阀
动网格
动态特性
斜激波
solid divert and attitude control system
gas valve
dynamic grid
dynamic characteristic
oblique shock wave
