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+
+//Variable Declaration
+
+PI=-1280  //I component of range vector for a satellite(km)
+PJ=-1278  //J component of range vector for a satellite(km)
+PK=66     //K component of range vector for a satellite(km)
+GST=240   //GST(degrees)
+LE=48.42  //Latitude(Degrees)
+PE=-89.26 //Longitude(Degrees)
+H=200     //Height above mean sea level(metres)
+aE=6378.1414 //Semimajor axis(km)
+eE=0.08182   //Eccentricity
+
+
+//Calculation
+
+l=(aE/sqrt(1-eE**2*sin(LE*3.142/180)**2)+H/1000)*cos(LE*3.142/180)  
+z=((aE*(1-eE**2))/sqrt(1-eE**2*sin(LE*3.142/180)**2)+H/1000)*sin(LE*3.142/180)  
+SE=(atan(z/l))*180/3.142 //Geocentric latitude angle (degrees)
+LST=240+PE
+
+
+a=sin(SE*3.142/180)*cos(LST*3.142/180)
+b=sin(SE*3.142/180)*sin(LST*3.142/180)
+c=-cos(SE*3.142/180)
+d=-sin(LST*3.142/180)
+e=cos(LST*3.142/180)
+f=0
+g=cos(SE*3.142/180)*cos(LST*3.142/180)
+h=cos(SE*3.142/180)*sin(LST*3.142/180)
+i=sin(SE*3.142/180)
+
+D = [a,b,c;d,e,f;g,h,i]
+
+P=  [PI;PJ;PK]
+
+R=D*P  //Components of range of earth station
+Ro=sqrt(R(1,1)**2+R(2,1)**2+R(3,1)**2) //Magnitude of range of earth station(km)
+El=asin(R(3,1)/Ro) //Antenna elevation angle for the earth station(radians) 
+El= El*180/3.142   //Converting El to degrees
+alpha=(atan(R(2,1)/R(3,1)))*180/3.142
+
+if ( R(1,1)<0 & R(2,1)>0 ) then
+   Aza=alpha
+else
+   Aza=0
+end   
+if ( R(1,1)>0 & R(2,1)>0 ) then
+   Azb=180-alpha
+else:
+   Azb=0
+end
+   
+if ( R(1,1)>0 & R(2,1)<0 ) then
+   Azc=180+alpha
+else
+   Azc=0
+end   
+if ( R(1,1)<0 & R(2,1)<0 ) then
+   Azd=360-alpha
+else
+   Azd=0
+end   
+Az= Aza+Azb+Azc+Azd   //Azimuth angle (degrees)
+
+printf("The magnitude of range of earth station is %.0f km",Ro)
+printf("\nThe antenna elevation angle for the earth station are %.f degrees",El)
+printf("\nThe Azimuth angle for the earth station is %.2f degrees",Az)