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针对超低地球轨道内外流一体化卫星和带孔空间碎片的气动特性分析与减阻设计问题,采用试验粒子Monte Carlo(TPMC)方法对200 km高度带头帽通孔圆柱体航天器外部绕流和内部流动并存问题进行模拟。结果表明:TPMC模拟结果与直接模拟Monte Carlo(DSMC)结果相一致,验证了TPMC方法的可靠性,以及对内外流并存问题的适用性;对于本文所考虑的内外流一体化问题,TPMC方法的计算速度是DSMC的2000余倍,消耗内存也比后者少1~2个量级;小攻角范围内,通孔的存在使得压阻分量减小,摩阻分量增大,综合效果是使阻力减小;外部表面对内孔表面的遮挡作用以及内孔表面之间的多次反射效应使内孔表面受到比较明显的压力,多次反射作用在轴向中部区域最强。
Aiming at the aerodynamic characteristics and drag reduction design of ultra-low-Earth orbit integrated orbit satellite with orbiting debris, the experimental particle Monte Carlo (TPMC) method is used to analyze the outer flow around a 200-km- Internal co-existence of mobile simulation. The results show that the TPMC simulation results are in good agreement with the direct simulation Monte Carlo (DSMC) results, which verify the reliability of the TPMC method and its applicability to the coexistence of internal and external flows. For the internal and external flow integration problems considered in this paper, The calculation speed is more than 2000 times of that of DSMC, and the memory consumption is also 1 ~ 2 orders of magnitude less than that of the latter. Within the small angle of attack, the existence of the through hole reduces the piezoresistive component and increases the friction component, The resistance of the inner surface decreases, the resistance of the outer surface to the inner hole surface and the multiple reflection effect between the inner hole surfaces make the inner hole surface subjected to more obvious pressure, and the multiple reflection effect is strongest in the axial middle area.