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//Variable Declaration
aE=6378.141 //Earth's equitorial radius(km)
e=0.002 //Eccentricity
p=12 //period from perigee to perigee (hours)
K1=66063.1704 //Constant (km^2)
u=3.986005*(10**14) //Earth's Gravitational constant(m^3/sec^2)
//Calculation
n=(2*%pi)/(12*60*60) //Mean Motion(rad/sec)
anp=((u/n**2)**(0.3333))/1000 //Radius of the orbit by kepler's 3rd law(km)
k2=(1-e**2)**1.5
function [y]=f(a)
y=(n-((u/a**3)**0.5)*(1+K1/a**2*k2))
endfunction
a=fsolve(2,f)
a=a/1000 //Converting a into km
//Result
printf("The nonperturbed value of semimajor axis is %.2f km",anp)
printf("\nThe perturbed value of semimajor axis is %.2f km",a)
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