Path: SC/Disturbances
% Compute the aerodynamic forces on a set of elemental areas.
The velocity vector and normal vectors must be in the same frame.
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Form:
[f,fT] = AeroF( rho, cD, v, normal, area )
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Inputs
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rho (1,1) Atmospheric density (kg/m3)
cD (1,1) Coefficient of drag
v (3,1) Velocity relative to the atmosphere (km/s)
normal (3,n) Surface normal vectors
area (n) Elemental area (m2)
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Outputs
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f (3,n) Aero force on elements (N)
fT (3,1) Total force on body
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Reference: Hughes, P. C., "Spacecraft Attitude Dynamics"
John Wiley and Sons, 1986, pp. 251.
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Math: Linear/Mag
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