matlab ode$45$ code to Determine the altitude decay per day of a set of satellites in circular orbits

ranging from $400$ km to $800$ km and whose mass properties are: Cd $=2\mathrm{.}2,$

S$/$m $=0\mathrm{.}01$ m$2/$kg$.$ In order to do that, use this simplified differential equation

for the rate of change of the semi$-$major axis:

da

dt $=2$s

a

$3$

$$

$\backslash$gamma f ;

where $\backslash$gamma f is the perturbed acceleration resultant from the effect of the atmospheric drag. Plot the deca