The study aimed to develop a two-dimensional numerical model of a perturbed Earth’s satellite orbit under the influence of the Moon. The first step was to model, numerically, the Earth-satellite orbit. The interaction was assumed to be first order. The basis of the model was that for two-dimensional motion, influence in the radial direction does not affect the motion in the tangential direction and vice versa. Based on this, the satellite’s motion was decomposed into radial and tangential directions. The trajectory was segmented into time intervals and the curve swept over each interval was approximated as a straight line with the assumption that acceleration in each interval was constant. Equations of constant accelerated motion were used to describe the motion of the satellite over each interval. When the model results were compared with the exact solution, for an elliptical orbit, they matched perfectly well over the entire orbit with a maximum relative error of 0.079%. When it was tested for other orbits, circular, hyperbolic, etc., it retained all of them according to theoretical predictions. The model was then extended to incorporate the effects of the Moon by launching the satellite at quarter, half and three-quarter distance from Earth to Moon. A circular orbit was used to model the effects of the Moon. The acceleration results of the model were compared with theoretical predictions. The corresponding errors in the acceleration for the three positions of launch were 0.019% and 0.20%. This showed that this model is applicable for predicting perturbated satellite orbit and it can be applied with any extra force to describe perturbated orbit of the satellite. It can also be used to model the trajectory of projectile motion, of which the exact solution is incapable of generating. Since this model gives the speed of the satellite at any instant, it can be applied when the orbit needs to be changed as it can be used to compute the required new speed.
Published in | International Journal of Applied Mathematics and Theoretical Physics (Volume 5, Issue 1) |
DOI | 10.11648/j.ijamtp.20190501.11 |
Page(s) | 1-14 |
Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
Copyright |
Copyright © The Author(s), 2019. Published by Science Publishing Group |
Two-Dimensional, Numerical, Model, Perturbation, Three-Body, Satellite, Orbit
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APA Style
Saneliso Vuyo Makhanya, Wei-Hsi Liao. (2019). Numerical Model of Perturbated Earth’s Satellite Orbit. International Journal of Applied Mathematics and Theoretical Physics, 5(1), 1-14. https://doi.org/10.11648/j.ijamtp.20190501.11
ACS Style
Saneliso Vuyo Makhanya; Wei-Hsi Liao. Numerical Model of Perturbated Earth’s Satellite Orbit. Int. J. Appl. Math. Theor. Phys. 2019, 5(1), 1-14. doi: 10.11648/j.ijamtp.20190501.11
AMA Style
Saneliso Vuyo Makhanya, Wei-Hsi Liao. Numerical Model of Perturbated Earth’s Satellite Orbit. Int J Appl Math Theor Phys. 2019;5(1):1-14. doi: 10.11648/j.ijamtp.20190501.11
@article{10.11648/j.ijamtp.20190501.11, author = {Saneliso Vuyo Makhanya and Wei-Hsi Liao}, title = {Numerical Model of Perturbated Earth’s Satellite Orbit}, journal = {International Journal of Applied Mathematics and Theoretical Physics}, volume = {5}, number = {1}, pages = {1-14}, doi = {10.11648/j.ijamtp.20190501.11}, url = {https://doi.org/10.11648/j.ijamtp.20190501.11}, eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijamtp.20190501.11}, abstract = {The study aimed to develop a two-dimensional numerical model of a perturbed Earth’s satellite orbit under the influence of the Moon. The first step was to model, numerically, the Earth-satellite orbit. The interaction was assumed to be first order. The basis of the model was that for two-dimensional motion, influence in the radial direction does not affect the motion in the tangential direction and vice versa. Based on this, the satellite’s motion was decomposed into radial and tangential directions. The trajectory was segmented into time intervals and the curve swept over each interval was approximated as a straight line with the assumption that acceleration in each interval was constant. Equations of constant accelerated motion were used to describe the motion of the satellite over each interval. When the model results were compared with the exact solution, for an elliptical orbit, they matched perfectly well over the entire orbit with a maximum relative error of 0.079%. When it was tested for other orbits, circular, hyperbolic, etc., it retained all of them according to theoretical predictions. The model was then extended to incorporate the effects of the Moon by launching the satellite at quarter, half and three-quarter distance from Earth to Moon. A circular orbit was used to model the effects of the Moon. The acceleration results of the model were compared with theoretical predictions. The corresponding errors in the acceleration for the three positions of launch were 0.019% and 0.20%. This showed that this model is applicable for predicting perturbated satellite orbit and it can be applied with any extra force to describe perturbated orbit of the satellite. It can also be used to model the trajectory of projectile motion, of which the exact solution is incapable of generating. Since this model gives the speed of the satellite at any instant, it can be applied when the orbit needs to be changed as it can be used to compute the required new speed.}, year = {2019} }
TY - JOUR T1 - Numerical Model of Perturbated Earth’s Satellite Orbit AU - Saneliso Vuyo Makhanya AU - Wei-Hsi Liao Y1 - 2019/02/15 PY - 2019 N1 - https://doi.org/10.11648/j.ijamtp.20190501.11 DO - 10.11648/j.ijamtp.20190501.11 T2 - International Journal of Applied Mathematics and Theoretical Physics JF - International Journal of Applied Mathematics and Theoretical Physics JO - International Journal of Applied Mathematics and Theoretical Physics SP - 1 EP - 14 PB - Science Publishing Group SN - 2575-5927 UR - https://doi.org/10.11648/j.ijamtp.20190501.11 AB - The study aimed to develop a two-dimensional numerical model of a perturbed Earth’s satellite orbit under the influence of the Moon. The first step was to model, numerically, the Earth-satellite orbit. The interaction was assumed to be first order. The basis of the model was that for two-dimensional motion, influence in the radial direction does not affect the motion in the tangential direction and vice versa. Based on this, the satellite’s motion was decomposed into radial and tangential directions. The trajectory was segmented into time intervals and the curve swept over each interval was approximated as a straight line with the assumption that acceleration in each interval was constant. Equations of constant accelerated motion were used to describe the motion of the satellite over each interval. When the model results were compared with the exact solution, for an elliptical orbit, they matched perfectly well over the entire orbit with a maximum relative error of 0.079%. When it was tested for other orbits, circular, hyperbolic, etc., it retained all of them according to theoretical predictions. The model was then extended to incorporate the effects of the Moon by launching the satellite at quarter, half and three-quarter distance from Earth to Moon. A circular orbit was used to model the effects of the Moon. The acceleration results of the model were compared with theoretical predictions. The corresponding errors in the acceleration for the three positions of launch were 0.019% and 0.20%. This showed that this model is applicable for predicting perturbated satellite orbit and it can be applied with any extra force to describe perturbated orbit of the satellite. It can also be used to model the trajectory of projectile motion, of which the exact solution is incapable of generating. Since this model gives the speed of the satellite at any instant, it can be applied when the orbit needs to be changed as it can be used to compute the required new speed. VL - 5 IS - 1 ER -