HI. I want to enter the orbital elements for the ISS based on real life positioning. I got the elements from http://calsky.com.
My question is on exactly how I should enter these into Orbiter
Kepler Elements
Semi-major Axis: 6730.773 km
Eccentricity: 0.0008685
Inclination: 51.6408°
Argument of Perigee: 246.9642°
Right Ascension of Ascending Node: 261.4942°
Mean Anomaly at Epoch: 257.7333°
Epoch (UTC): 16. Apr 2009 19:43:12 (JD=2454938.32166763)
I assume that since the Inc is 51°, this is all based on
the equatorial frame so I should set that first.
Since it is the Equ fram, RAofAN is the LAN right? If so, is
Lpe then RAoAN + Argument of Perigee and
eps RAoAN + Mean Anomaly at Epoch?
I assume then, for Epoch, I should enter in the
JD - 2400000.5 right?
Thanks,
Paul
My question is on exactly how I should enter these into Orbiter
Kepler Elements
Semi-major Axis: 6730.773 km
Eccentricity: 0.0008685
Inclination: 51.6408°
Argument of Perigee: 246.9642°
Right Ascension of Ascending Node: 261.4942°
Mean Anomaly at Epoch: 257.7333°
Epoch (UTC): 16. Apr 2009 19:43:12 (JD=2454938.32166763)
I assume that since the Inc is 51°, this is all based on
the equatorial frame so I should set that first.
Since it is the Equ fram, RAofAN is the LAN right? If so, is
Lpe then RAoAN + Argument of Perigee and
eps RAoAN + Mean Anomaly at Epoch?
I assume then, for Epoch, I should enter in the
JD - 2400000.5 right?
Thanks,
Paul