CL_cw_diffDrag — Differential acceleration drag
[acc_diff]=CL_cw_diffDrag(altitude,cbal1,cbal2[,er,mu])
spacecraft (target) altitude [m] (1xN)
target ballistic coefficient S*cx/m S=equivalent drag surface, cx = drag coefficient, m = mass [m^2/kg] (1xN)
chaser ballistic coefficient S*cx/m S=equivalent drag surface, cx = drag coefficient, m = mass [m^2/kg] (1xN)
(optional) equatorial radius [m] (default is %CL_eqRad)
(optional) geocentric gravitational constant [m^3/s^2] (default value is %CL_mu)
differential acceleration [m/s^2] (1xN)