Ephemeris Files
These files contain the ephemerides for various satellites analyzed in the paper An Analysis of State Vector Propagation Using Differing Flight Dynamics Programs
by David A. Vallado. Each satellite includes individual force model ephemerides for comparison. All satellite orbital information is approximate as epochs and physical characteristics are kept constant to permit better comparison to other satellites.
| 25544—ISS |
Apogee altitude = 389km |
Perigee altitude = 377km |
| 00011—Vanguard 2 |
Apogee altitude = 3023km |
Perigee altitude = 550km |
| 20052—Molnyia 3-35 |
Apogee altitude = 38026km |
Perigee altitude = 285km |
| 21867—JERS |
Apogee altitude = 38026km |
Perigee altitude = 285km |
| 22076—TOPEX |
Apogee altitude = 1347km |
Perigee altitude = 1340km |
| 25054—SL-12 RB |
Apogee altitude = 21371km |
Perigee altitude = 186km |
| 26038—Galaxy 11 |
Apogee altitude = 35785km |
Perigee altitude = 35790km |
| 26690—NAVSTAR 50 |
Apogee altitude = 20282km |
Perigee altitude = 20082km |
The following file contains the figures of the force model evaluation runs. Each plot shows the effect of
different force models compared to a common 12 x 12 EGM-96 gravity field.
The following file uses the proposed format to convey the setup information for each of the satellites listed above.
Formats
Proposed State Vector Format The following file is the proposed format to convey the setup information for transferring state vector information.
Community Ephemeris Baseline The following file uses the proposed format to convey the setup information for each of the satellites listed above.
If additional tests, integrators, force models, etc., are desired, please contact cssi@CenterForSpace.com.
