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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)
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