使用圆柱坐标系网格的三维DSMC(Direct Simulation Monte Carlo)模型,对同轴圆柱间Taylor-Couette流中Taylor涡的形成进行了数值模拟,并分析了不同计算域和边界条件下稳定流场中Taylor涡的轴向排列结构.在网格设置和流场参数不变的情况...使用圆柱坐标系网格的三维DSMC(Direct Simulation Monte Carlo)模型,对同轴圆柱间Taylor-Couette流中Taylor涡的形成进行了数值模拟,并分析了不同计算域和边界条件下稳定流场中Taylor涡的轴向排列结构.在网格设置和流场参数不变的情况下,使用轴对称DSMC模型对Taylor涡进行数值模拟,所得Taylor涡的稳定过程与三维结果一致,验证了使用三维DSMC方法来解决微尺度低速的稀薄气流问题的可行性.三维模拟结果表明Taylor涡以较大的圆周速度绕轴旋转,二维模拟则无法体现.对不同的内圆柱旋转速度进行数值模拟,确定了能够产生Taylor涡的临界速度值.展开更多
This paper uses a direct simulation Monte Carlo （DSMC） approach to simulate rarefied aerodynamic characteristics during the aerobraking process of the NASA Mars Global Surveyor （MGS） spacecraft. The research focus...This paper uses a direct simulation Monte Carlo （DSMC） approach to simulate rarefied aerodynamic characteristics during the aerobraking process of the NASA Mars Global Surveyor （MGS） spacecraft. The research focuses on the flowfield and aerodynamic characteristics distribution under various free stream densities. The vari- ation regularity of aerodynamic coefficients is analyzed. The paper also develops an aerodynamics-aeroheating-trajectory integrative simulation model to preliminarily calculate the aerobraking orbit transfer by combining the DSMC technique and the classical kinematics theory. The results show that the effect of the planetary atmospheric density, the spacecraft yaw, and the pitch attitudes on the spacecraft aerodynamics is significant. The numerical results are in good agreement with the existing results reported in the literature. The aerodynamics-aeroheating-trajectory integrative simulation model can simulate the orbit transfer in the complete aerobraking mission. The current results of the spacecraft trajectory show that the aerobraking maneuvers have good performance of attitude control.展开更多
气溶胶动力学方程是描述气溶胶动力学变化的主要方程,凝并与沉降共存问题是相关领域的常见的问题。建立了对该类问题的分段算法和直接蒙特卡罗模拟(Direct Simulation Monte Carlo method,DSMC)计算方法,对DSMC中事件后系统参数的更新...气溶胶动力学方程是描述气溶胶动力学变化的主要方程,凝并与沉降共存问题是相关领域的常见的问题。建立了对该类问题的分段算法和直接蒙特卡罗模拟(Direct Simulation Monte Carlo method,DSMC)计算方法,对DSMC中事件后系统参数的更新方法进行了改进,并提出了用纳入解析解的分段算法的结果对DSMC模拟结果进行验证的方法。结果表明,改进的DSMC算法显著提高了计算效率,模拟结果与其它算法的结果一致。展开更多
文摘使用圆柱坐标系网格的三维DSMC(Direct Simulation Monte Carlo)模型,对同轴圆柱间Taylor-Couette流中Taylor涡的形成进行了数值模拟,并分析了不同计算域和边界条件下稳定流场中Taylor涡的轴向排列结构.在网格设置和流场参数不变的情况下,使用轴对称DSMC模型对Taylor涡进行数值模拟,所得Taylor涡的稳定过程与三维结果一致,验证了使用三维DSMC方法来解决微尺度低速的稀薄气流问题的可行性.三维模拟结果表明Taylor涡以较大的圆周速度绕轴旋转,二维模拟则无法体现.对不同的内圆柱旋转速度进行数值模拟,确定了能够产生Taylor涡的临界速度值.
基金Project supported by the Aerospace Foundation of China Academy of Space Technology (No.CAST2006023)
文摘This paper uses a direct simulation Monte Carlo （DSMC） approach to simulate rarefied aerodynamic characteristics during the aerobraking process of the NASA Mars Global Surveyor （MGS） spacecraft. The research focuses on the flowfield and aerodynamic characteristics distribution under various free stream densities. The vari- ation regularity of aerodynamic coefficients is analyzed. The paper also develops an aerodynamics-aeroheating-trajectory integrative simulation model to preliminarily calculate the aerobraking orbit transfer by combining the DSMC technique and the classical kinematics theory. The results show that the effect of the planetary atmospheric density, the spacecraft yaw, and the pitch attitudes on the spacecraft aerodynamics is significant. The numerical results are in good agreement with the existing results reported in the literature. The aerodynamics-aeroheating-trajectory integrative simulation model can simulate the orbit transfer in the complete aerobraking mission. The current results of the spacecraft trajectory show that the aerobraking maneuvers have good performance of attitude control.
文摘气溶胶动力学方程是描述气溶胶动力学变化的主要方程,凝并与沉降共存问题是相关领域的常见的问题。建立了对该类问题的分段算法和直接蒙特卡罗模拟(Direct Simulation Monte Carlo method,DSMC)计算方法,对DSMC中事件后系统参数的更新方法进行了改进,并提出了用纳入解析解的分段算法的结果对DSMC模拟结果进行验证的方法。结果表明,改进的DSMC算法显著提高了计算效率,模拟结果与其它算法的结果一致。
