Change of right ascension of the ascending node of medium Earth orbits with constant semi-major axis and different eccentricity
Authors: Ivanov S.G., Grishko D.A., Baranov A.A.
Published in issue: #9(153)/2024
DOI: 10.18698/2308-6033-2024-9-2383
Category: Mechanics | Chapter: Theoretical Mchanics, Machine Dynamics
The paper presents the results of studying the energy costs required to correct the Right Ascension of the Ascending Node (RAAN) of the orbit of an object initially located at the operation altitudes of GLONASS and GPS global navigation satellite systems. Two types of problems are considered. In the first case, the rotation of the plane of motion is performed for a family of elliptical orbits with a constant semi-major axis, while the eccentricity may vary due to gravitational perturbations from the Moon and the Sun. In the second case, near-circular orbits with the same values of the semi-major axes are studied, and the transfer of an object to another operating plane with the same inclination is considered using a drift orbit with a different period. The research methods are based on the basic principles of spherical trigonometry and the theory of spacecraft manoeuvring. It is shown that the lowest cost of orbital plane orientation correction is achieved at large eccentricity values when the apocentre position coincides with the intersection points of the initial and final orbits. If the eccentricity value is small, the introduction of a near-circular drift orbit below/above the object's operating altitude, leads to a decrease in the characteristic velocity required to change the RAAN compared to impulse correction. The greatest effect is achieved when the orbit plane is to be rotated in the direction of the natural precession of the RAAN. The choice of the parameters of the drift orbit itself deserves special attention.
The study was supported by a grant from the Russian Science Foundation
No. 23-29-00419, https://rscf.ru/project/23-29-00419/
EDN MWTRTB
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