Path: FormationFlying/Collision
% Relative disturbances for use with a relative state. -------------------------------------------------------------------------- Form: aDiff = RelativeDisturb( jD, r, v, dr, dA, mSC, Cd, Cr, iRef ) -------------------------------------------------------------------------- ------ Inputs: ------- jD (1,1) Epoch (Julian date) r (3,1) Reference position in ECI frame (km) v (3,1) Reference velocity in ECI frame (km/s) dr (3,1) Relative position between the spacecraft (km) dA (1,1) Differential area between the spacecraft (m2) mSC (1,1) Mass spacecraft (kg) Cd (1,1) Drag coefficient Cr (1,1) Reflection coefficient iRef (1,1) Reference inclination (rad) ------- Outputs: -------- aDiff (3,1) sum of all the terms (m/s/s) --------------------------------------------------------------------------