Fourier Series Approximations to J2-Bounded Equatorial Orbits
The current paper offers a comprehensive dynamical analysis and Fourier series approximations of J2-bounded equatorial orbits. The initial conditions of heterogeneous families of J2-perturbed equatorial orbits are determined first. Then the characteristics of two types of J2-bounded orbits, namely,...
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Series: | Mathematical Problems in Engineering |
Online Access: | http://dx.doi.org/10.1155/2014/568318 |
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doaj-29741e4c1e9846e092aea9f5a96b3c362020-11-25T01:36:02ZengHindawi LimitedMathematical Problems in Engineering1024-123X1563-51472014-01-01201410.1155/2014/568318568318Fourier Series Approximations to J2-Bounded Equatorial OrbitsWei Wang0Jianping Yuan1Yanbin Zhao2Zheng Chen3Changchun Chen4Research and Development Center, Shanghai Institute of Satellite Engineering, Shanghai 200240, ChinaCollege of Astronautics, Northwestern Polytechnical University, Xi’an 710072, ChinaResearch and Development Center, Shanghai Institute of Satellite Engineering, Shanghai 200240, ChinaCollege of Astronautics, Northwestern Polytechnical University, Xi’an 710072, ChinaResearch and Development Center, Shanghai Institute of Satellite Engineering, Shanghai 200240, ChinaThe current paper offers a comprehensive dynamical analysis and Fourier series approximations of J2-bounded equatorial orbits. The initial conditions of heterogeneous families of J2-perturbed equatorial orbits are determined first. Then the characteristics of two types of J2-bounded orbits, namely, pseudo-elliptic orbit and critical circular orbit, are studied. Due to the ambiguity of the closed-form solutions which comprise the elliptic integrals and Jacobian elliptic functions, showing little physical insight into the problem, a new scheme, termed Fourier series expansion, is adopted for approximation herein. Based on least-squares fitting to the coefficients, the solutions are expressed with arbitrary high-order Fourier series, since the radius and the flight time vary periodically as a function of the polar angle. As a consequence, the solutions can be written in terms of elementary functions such as cosines, rather than complex mathematical functions. Simulations enhance the proposed approximation method, showing bounded and negligible deviations. The approximation results show a promising prospect in preliminary orbits design, determination, and transfers for low-altitude spacecrafts.http://dx.doi.org/10.1155/2014/568318 |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Wei Wang Jianping Yuan Yanbin Zhao Zheng Chen Changchun Chen |
spellingShingle |
Wei Wang Jianping Yuan Yanbin Zhao Zheng Chen Changchun Chen Fourier Series Approximations to J2-Bounded Equatorial Orbits Mathematical Problems in Engineering |
author_facet |
Wei Wang Jianping Yuan Yanbin Zhao Zheng Chen Changchun Chen |
author_sort |
Wei Wang |
title |
Fourier Series Approximations to J2-Bounded Equatorial Orbits |
title_short |
Fourier Series Approximations to J2-Bounded Equatorial Orbits |
title_full |
Fourier Series Approximations to J2-Bounded Equatorial Orbits |
title_fullStr |
Fourier Series Approximations to J2-Bounded Equatorial Orbits |
title_full_unstemmed |
Fourier Series Approximations to J2-Bounded Equatorial Orbits |
title_sort |
fourier series approximations to j2-bounded equatorial orbits |
publisher |
Hindawi Limited |
series |
Mathematical Problems in Engineering |
issn |
1024-123X 1563-5147 |
publishDate |
2014-01-01 |
description |
The current paper offers a comprehensive dynamical analysis and Fourier series approximations of J2-bounded equatorial orbits. The initial conditions of heterogeneous families of J2-perturbed equatorial orbits are determined first. Then the characteristics of two types of J2-bounded orbits, namely, pseudo-elliptic orbit and critical circular orbit, are studied. Due to the ambiguity of the closed-form solutions which comprise the elliptic integrals and Jacobian elliptic functions, showing little physical insight into the problem, a new scheme, termed Fourier series expansion, is adopted for approximation herein. Based on least-squares fitting to the coefficients, the solutions are expressed with arbitrary high-order Fourier series, since the radius and the flight time vary periodically as a function of the polar angle. As a consequence, the solutions can be written in terms of elementary functions such as cosines, rather than complex mathematical functions. Simulations enhance the proposed approximation method, showing bounded and negligible deviations. The approximation results show a promising prospect in preliminary orbits design, determination, and transfers for low-altitude spacecrafts. |
url |
http://dx.doi.org/10.1155/2014/568318 |
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