HIGH ACCURACY SPACECRAFT ORBIT PROPAGATOR VALIDATION | ||
| The International Conference on Applied Mechanics and Mechanical Engineering | ||
| Article 16, Volume 18, 18th International Conference on Applied Mechanics and Mechanical Engineering., April 2018, Pages 1-9 PDF (272.24 K) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/amme.2018.34732 | ||
| Authors | ||
| A. Refaat1; A. Badawy2; M. Ashry1; Adel Omar1 | ||
| 1Egyptian Armed Forces. | ||
| 2Assoc. Prof., October University for Modern Sciences and Arts (MSA), Egypt. | ||
| Abstract | ||
| ABSTRACT The Space Situational Awareness (SSA) problem is becoming an exponentially significant concern for satellite operators. The threat of on-orbit collisions endangers satellites, spacecrafts and astronauts themselves especially in low-earth orbits (LEO). Many collisions occurred between satellites and debris that include natural, operational and non-operational objects in space. The collision between Russian cosmos 2251 and American iridium 33, for instance, imposed the need for an accurate orbital propagation module. In order to perform successful collision avoidance maneuvers, the mission operators need the orbit prediction to be highly accurate. Simple impractical number of collision avoidance maneuvers represents dreadful solution to escape of collision. Fake warning means waste of fuel and resources of satellite. This paper introduces an enhanced model to increase the accuracy of propagation estimation based on a precise perturbation model. | ||
| Keywords | ||
| Orbit; propagation; Drag; TLE; Cowell; STK; SGP4; hpop; eclipse; ephemerides | ||
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