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//Variable Declaration
NN=14.22296917 //Mean Motion (1/day)
u=3.986005*(10**14) //Earth's Gravitational COnstant(m^3/sec^2)
//Calculation
n0=(NN*2*3.142)/(24*60*60) //Mean Motion(rad/sec)
a=((u/n0**2)**(0.33333))/1000 //Radius of the orbit by kepler's 3rd law(km)
//Result
printf("The Semimajor axis for given satellite parameters is : %.2f km",a)
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