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Crude Atmospheric Drag Calculations

Crude Atmospheric Drag Calculations. Crudely approximated the atmospheric drag of the ISS (4.8 *10 6 ) using the orbital velocity (25285 ft/s) and density of 100km (3.75*10 -7 slug/ft 3 )

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Crude Atmospheric Drag Calculations

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  1. Crude Atmospheric Drag Calculations • Crudely approximated the atmospheric drag of the ISS (4.8 *106) using the orbital velocity (25285 ft/s) and density of 100km (3.75*10-7slug/ft3) • Estimated the wetted area of the upper stage (1 m2) used the same orbital velocity of the ISS and the density at 100km • Used this crude approximation to estimate a rough atmospheric drag of the upper stage (237)

  2. How to refine estimates • Matlab code provided to estimate the atmospheric and solar drag of the upper stage • This code will be available week of 2/18 • ISS “falls” out of orbit by 2.5km per month. Upper stage will need to follow. • Add solar/atmospheric drag with losses due to navigational error to refine the fuel requirements of the mission

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