Comparison of Orbit Propagators in the Research and Development Goddard Trajectory Determination System (R & D GTDS). Part 1. Simulated Data
NAVAL POSTGRADUATE SCHOOL MONTEREY CA DEPT OF MATHEMATICS
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This paper evaluates the performance of various orbit propagation theories for artificial earth satellites in different orbital regimes. Specifically, RD GTDSs Cowell numerical technique, DSST semianalytical technique, SGP, SGP4, and Brouwer-Lyddane analytic techniques orbit propagators are compared for decaying circular approx. 200 km perigee height, low altitude circular 590 km perigee height, high altitude circular 1340 km perigee height, Molniya, and geosynchronous orbits. All test cases implement a one orbital period differential correction fit to simulated data derived from a Cowell truth trajectory. These fits are followed by a one orbital period predict with the DC solve-for vector.
- Numerical Mathematics
- Computer Programming and Software
- Spacecraft Trajectories and Reentry