An Orbit Propagation Software for Mars Orbiting Spacecraft
| Autor: | Jae-Cheol Yoon, Byung-Kyo Kim, Jo-Ryeong Yim, Sang Young Park, Han-Dol Kim, Hak-Jung Kim, Jun-Min Choi, Young-Joo Song, Eunseo Park, Kyu-Hong Choi, Sung-Moon Yoo |
|---|---|
| Jazyk: | angličtina |
| Rok vydání: | 2004 |
| Předmět: |
Physics
Spacecraft business.industry lcsh:Astronomy Nutation Mars coordinate system General Physics and Astronomy Mars Mars Exploration Program Ephemeris Exploration of Mars Aerobraking lcsh:QB1-991 Planet Physics::Space Physics General Earth and Planetary Sciences Timekeeping on Mars orbit propagation software Astrophysics::Earth and Planetary Astrophysics Aerospace engineering business perturbations near Mars Remote sensing |
| Zdroj: | Journal of Astronomy and Space Sciences, Vol 21, Iss 4, Pp 351-360 (2004) |
| ISSN: | 2093-1409 2093-5587 |
| Popis: | An orbit propagation software for the Mars orbiting spacecraft has been developed and verified in preparations for the future Korean Mars missions. Dynamic model for Mars orbiting spacecraft has been studied, and Mars centered coordinate systems are utilized to express spacecraft state vectors. Coordinate corrections to the Mars centered coordinate system have been made to adjust the effects caused by Mars precession and nutation. After spacecraft enters Sphere of Influence (SOI) of the Mars, the spacecraft experiences various perturbation effects as it approaches to Mars. Every possible perturbation effect is considered during integrations of spacecraft state vectors. The Mars50c gravity field model and the Mars-GRAM 2001 model are used to compute perturbation effects due to Mars gravity field and Mars atmospheric drag, respectively. To compute exact locations of other planets, JPL's DE405 ephemerides are used. Phobos and Deimos's ephemeris are computed using analytical method because their informations are not released with DE405. Mars Global Surveyor's mapping orbital data are used to verify the developed propagator performances. After one Martian day propagation (12 orbital periods), the results show about maximum ±5 meter errors, in every position state components(radial, cross-track and along-track), when compared to these from the Astrogator propagation in the Satellite Tool Kit. This result shows high reliability of the developed software which can be used to design near Mars missions for Korea, in future. |
| Databáze: | OpenAIRE |
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