Analytic solution to the relative orbital motion around an oblate planet

Analytic solution; Closed-form expression; Initial conditions; Oblateness; Orbital element; Orbital motions; Reference frame; Relative positions; Relative velocity; Satellites formation; Navigation; Satellites

Abstract :

[en] The paper offers a vectorial approach to the J2-perturbed relative orbital motion. The model uses mean orbital elements in order to derive closed form expressions for the relative position and relative velocity with respect to the LVLH frame attached on a main satellite. The advantage of the present approach is that only the motion of one satellite must be known, together with the initial conditions with respect to LVLH of the other satellites. As in the previous works of the authors, a tensorial instrument is used in order to transfer the motion from inertial to non-inertial reference frames and back. In this way, a concise instrument for the study of the satellites formations under the influence of the oblateness factor J2 is offered. Copyright © 2009 by Daniel Condurache and Vladimir Martinusi.

Disciplines :

Aerospace & aeronautics engineering

Author, co-author :

Condurache, D.; Technical University Gheorghe Asachi, Department of Theoretical Mechanics, Iasi, Romania

Martinusi, Vladimir ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Laboratoire de structures et systèmes spatiaux

Title :

Analytic solution to the relative orbital motion around an oblate planet

Publication date :

2009

Event name :

AIAA Guidance, Navigation, and Control Conference and Exhibit

Event date :

10 August 2009 through 13 August 2009

Audience :

International

Journal title :

AIAA Guidance, Navigation, and Control Conference and Exhibit

Commentary :

81960 9781563479786

Available on ORBi :

since 12 February 2015

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Bibliography

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