DRAG COEFFICIENT MODELING FOR GRACE USING DIRECT SIMULATION MONTE CARLO

被引：0
|
作者：
Mehta, Piyush M. [1 ]
McLaughlin, Craig A. [1 ]
机构：
[1] Univ Kansas, Dept Aerosp Engn, 1530 W 15th St, Lawrence, KS 66045 USA
来源：
SPACEFLIGHT MECHANICS 2013, PTS I-IV | 2013年 / 148卷
关键词：
GAS-SURFACE INTERACTIONS;
D O I：
暂无
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The drag coefficient of a satellite in low Earth orbit is dependent on the gas-surface interactions, attitude, satellite geometry, spacecraft relative velocity, atmospheric composition, atmospheric temperature, and spacecraft surface properties. The Direct Simulation Monte Carlo code, DS3V, is used to develop a drag coefficient model for GRACE. The code is validated with the analytical solution for the drag coefficient of a flat plate, sphere, and cylinder and drag coefficients derived for GRACE using a flat plate model. The energy-accommodation model assumes diffuse gas-surface interactions.
引用
收藏
页码：1281 / 1298
页数：18
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