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...
| Главный автор: | |
|---|---|
| Формат: | Статья |
| Язык: | English |
| Опубликовано: |
University of Anbar
2020-06-01
|
| Серии: | مجلة جامعة الانبار للعلوم الصرفة |
| Предметы: | |
| Online-ссылка: | https://juaps.uoanbar.edu.iq/article_172315_555a240eca3adf0f37d0a1b9c4fe64dd.pdf |