摘要
航天运载器在70 km以上高空高速飞行,火箭发动机的喷流是影响其尾舱热环境的主要因素之一。采用代数方程和偏微分方程相结合的多块网格生成方法,达到热流计算中对近壁面网格的正交性和分布上的要求;通过改进的NND有限体积法高超程序,数值耦合求解多组分NS方程、湍流方程、热辐射方程和非平衡化学反应方程,提高了壁面热流计算的精度。计算结果与飞行遥测及地面实验结果对比分析表明,所采用的计算方法及得到的结果是正确有效的。
When launch vehicle is flying at the altitude above 70kin, the jet flow of its rocket engine is one of the main masons that affect the heat circumstance of its second tail comparment. In order to simulation such a complicated problem, multiple block mesh is generated by algebraic method and the Partial Differential Equation （PDE） method, which satisfies the requirements of high quality mesh to compute heat flux. By revised NND finite volume method hypersonic program, coupled solution to the multiple species NS equations, turbulence equations, radiation equations and non-equilibrium reaction, the accuracy of wall heat flux calculation is enhanced. By contrastive analysis on the numerical simulation result, ground test and remote sensing test proves that the computing method and the result are right and available.
出处
《导弹与航天运载技术》
北大核心
2008年第4期11-15,共5页
Missiles and Space Vehicles
关键词
高空喷流
热辐射
非平衡化学反应
计算流体力学
High altitude jet
Heat radiation
Nonequilibrium reaction
Computational fluid dynamics
