STEP 14: SATELLITE'S EQUATORIAL

a, d



 
Element Symbol Value
Epoch to 05:54:21.171 UTC December 16, 2007
Inclination i 51o.9970
R.A. of the Ascending Node aW0 251o.0219
Eccentricity e 0.0001492
Argument of Perigee w0 33o.8641
Mean Anomaly at TLE Epoch Mo 326o.2322
Mean Motion n 12.62256095 orbits / solar day
Propagation Time Dt 1.7677141 solar days
Mean Anomaly at Time t M(t) 1.37777389 radians (78o.940629)
True Anomaly at Time t n(t) 78o.95065818
Semi-major Axis a 7791.787473 km
Perigee Distance P 7790.624938 km
Geocentric Distance r(t) 7791.564499 km
Precessed R.A. of Asc. Node aW(t) 245o.6400244
Precessed Arg. of Perigee w(t) 37o.77767416
Argument of Latitude m(t) 116o.7283323
R.A. Difference Da 129o.278845
Geocentric R.A. ag 14o.9188694
Geocentric Declination dg +44o.73125163
Geocentric Cartesian x xg 5348.663965 km
Geocentric Cartesian y yg 1425.05581 km
Geocentric Cartesian z zg 5483.565179 km
Observer Geodetic Longitude q -75o.6883
Observer Geodetic Latitude l +44o.5903
Observer Geocentric Dec. di +44o.5903
Observer Geocentric R.A. ai 15o.419875
Observer Geocentric Cart. x ag 4371.468712 km
Observer Geocentric Cart. y bg 1205.734692 km
Observer Geocentric Cart. z cg 4470.310913 km


The Topocentric Cartesian Coordinates of the satellite can be determined by using the following equations:

xs = xg - ag
ys = yg - bg
zs = zg - cg

xs = 977.195253 km
ys = 219.321118 km
zs = 1013.254266 km

Finally, the Topocentric Equatorial Coordinates of the GlobalStar M047 satellite as seen from the observing location on the Earth can now be calculated using the following equations. The calculation of the Topocentric Right Ascension is dependant on conditions that relate to which quadrant the satellite is in at the time:

a = tan-1 [ ys / xs ]
FOR ys>0 AND xs>0

a = 180o + tan-1 [ ys / xs ]
FOR xs<0

a = 360o + tan-1 [ ys / xs ]
FOR ys<0 AND xs>0

r = [ xs2 + ys2 + zs2 ]1/2
d = sin-1 [ zs / r ]

r = 1424.674181 km
a = 12o.64980763 = 00h 50m 35s.95
d = +45o.32255686 = +45o 20' 02".84
 

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Step 14: Satellite's Equatorial Was Last Modified On May 29, 2015