Center For Space Standards & Innovation

Downloads

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.