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Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit
W. A. Rahoma 한국우주과학회 2014 Journal of Astronomy and Space Sciences Vol.31 No.3
This paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the second order using Legendre polynomials. A double-averaged analytical model is exploited to produce the evolutions of mean orbital elements as smooth curves.
Orbital Elements Evolution Due to a Perturbing Body in an Inclined Elliptical Orbit
Rahoma, W.A The Korean Space Science Society 2014 Journal of Astronomy and Space Sciences Vol.31 No.3
This paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the second order using Legendre polynomials. A double-averaged analytical model is exploited to produce the evolutions of mean orbital elements as smooth curves.