NDLI: Algebraic orbit elements difference description of dynamics models for satellite formation flying

Content Provider	IEEE Xplore Digital Library
Author	Navabi, M. Barati, M. Bonyan, H.
Copyright Year	2013
Description	Author affiliation: Fac. of New Technol. Eng., Shahid Beheshti Univ., Tehran, Iran (Navabi, M.; Barati, M.; Bonyan, H.)
Abstract	In recent years, spacecraft formation flying has turn to a feasible solution to achieve improvements in performance and capabilities of space assets. As a result, dynamics of satellite formations has become an active area of research. To take full advantage of the benefits offered by formation flying concepts, it is necessary to develop and examine its dynamics models. In this paper, four models in terms of orbital elements namely Nonlinear Orbit Element Model, Linear Orbit Element Model, Linear Small eccentricity Orbit Element Model and Linear Circular Orbit Element Model are studied. An error index is given to measure accuracy of each model compared to the nonlinear model as the reference. This is performed by investigating the effects of main error sources in LEO orbits on the accuracy of formation modeling. These error sources are Earth gravitational perturbation, formation size and eccentricity of chief orbit. Based on the simulation results, one may be able to choose the appropriate model according to the desired accuracy for a given mission.
Sponsorship	IEEE Aerosp. Electron. Syst. Soc.
Starting Page	277
Ending Page	280
File Size	913219
Page Count	4
File Format	PDF
ISBN	9781467363952
e-ISBN	9781467363969
DOI	10.1109/RAST.2013.6581216
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2013-06-12
Publisher Place	Turkey
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	formation flying Extraterrestrial measurements satellite dynamics modeling
Content Type	Text
Resource Type	Article

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