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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)
+
+