کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
5486680 | 1399472 | 2017 | 16 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
Trajectory refinement of three-body orbits in the real solar system model
ترجمه فارسی عنوان
پالایش مسیر در مدار سه ذره در مدل منظم منظومه شمسی
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موضوعات مرتبط
مهندسی و علوم پایه
علوم زمین و سیارات
علوم فضا و نجوم
چکیده انگلیسی
In this paper, an automatic algorithm for the correction of orbits in the real solar system model is described. The differential equations governing the dynamics of a massless particle in the n-body problem are written as perturbation of the circular restricted three-body problem in a non-uniformly rotating, pulsating frame by using a Lagrangian formalism. The refinement is carried out by means of a modified multiple shooting technique, and the problem is solved for a finite number of trajectory states at several time instants. The analysis involves computing the dynamical substitutes of the collinear points, as well as several Lagrange point orbits, for the Sun-Earth, Sun-Jupiter, and Earth-Moon gravitational systems.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Advances in Space Research - Volume 59, Issue 8, 15 April 2017, Pages 2117-2132
Journal: Advances in Space Research - Volume 59, Issue 8, 15 April 2017, Pages 2117-2132
نویسندگان
Diogene A. Dei Tos, Francesco Topputo,