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

页码：1281 / 1298

页数：18

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