摘要
考虑到实际卫星总体布局特点及姿控发动机燃气喷流为多组分的特点,采用差分求解N-S(Navier-Stokes)方程耦合DSMC(Direct Simulation Monte Carlo)方法建立三维多组分羽流场的数值模拟模型,对5 N无水肼单组元姿控发动机喷管产生的燃气羽流场及其效应进行数值模拟,计算得出羽流场的物理参数分布、化学组分分布,得到了羽流对太阳能帆板的羽流气动力和气动热效应.计算结果表明对于太阳能帆板的羽流效应防护应以N2,NH3为主,姿控发动机羽流会对太阳能帆板撞击产生气动力和气动热的影响,在太阳能帆板前沿中点处,存在气动压强峰值和气动热流峰值.计算结果为研究羽流效应提供了参考依据.
To simulate actual attitude control thruster plume flow and its effects, the three-dimensional plume effects were studied by the approach which combines difference solution of Navier-Stokes（N-S） equations and the three-dimension mixture gases direct simulation Monte Carlo method（ DSMC）, according to the layout of the thruster on the satellite and actual attitude control thruster＇s exhaust consisting of mixture gases. The plume parameters of the flow field, aerodynamic force and aerodynamic thermal effects to solar cells were obtained for a 5 N hydrazine satellite attitude control thruster. The result shows that N2 and NH3 should be paid more attention for the plume effects＇ protection of solar cells and the plume can bring the force and thermal effects on the solar cells. The peak value of aerodynamic force and aerodynamic thermal effects is on the front of the solar cells. The work is helpful for the plume effects research.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2010年第2期154-158,共5页
Journal of Beijing University of Aeronautics and Astronautics
基金
民用航天预先研究资助项目(WB1.19)
国防预研资助项目(41320060102)
新世纪优秀人才计划项目
关键词
卫星姿控发动机
多组分
真空
羽流
三维
数值模拟
attitude control thruster
mixture gases
vacuum
plume
three dimension
numerical simu- lation
