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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Main Authors: Wei Wang, Jianping Yuan, Yanbin Zhao, Zheng Chen, Changchun Chen
Format: Article
Language:English
Published: Hindawi Limited 2014-01-01
Series:Mathematical Problems in Engineering
Online Access:http://dx.doi.org/10.1155/2014/568318
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spelling 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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AT zhengchen fourierseriesapproximationstoj2boundedequatorialorbits
AT changchunchen fourierseriesapproximationstoj2boundedequatorialorbits
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