Modification of Three Order Methods For Solving Satellite Orbital Equation in Elliptical Motion
In the present study, a modification for iterative methods of three order is presented by means of mean anomaly to calculate the values of E and e (true anomaly and eccentricity) respectively, for a planet in an elliptical orbit around the sun. We find that the improved methods converge to the true...
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| Format: | Članak |
| Jezik: | English |
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University of Anbar
2020-06-01
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| Serija: | مجلة جامعة الانبار للعلوم الصرفة |
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| Online pristup: | https://juaps.uoanbar.edu.iq/article_172315_555a240eca3adf0f37d0a1b9c4fe64dd.pdf |