DRAG COEFFICIENT MODELING FOR GRACE USING DIRECT SIMULATION MONTE CARLO

摘要

The drag coefficient of a satellite in low Earth orbit is dependent on thegas-surface interactions, attitude, satellite geometry, spacecraft relative velocity,atmospheric composition, atmospheric temperature, and spacecraft surfaceproperties. The Direct Simulation Monte Carlo code, DS3V, is used to developa drag coefficient model for GRACE. The code is validated with the analyticalsolution for the drag coefficient of a flat plate, sphere, and cylinder and dragcoefficients derived for GRACE using a flat plate model. The energy-accommodationmodel assumes diffuse gas-surface interactions.