Minimal Thrusters Configuration for Simultaneous Orbit Correction and Reaction Wheels Desaturation for GEO Satellite
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mal Thrusters Configuration for Simultaneous Orbit Correction and Reaction Wheels Desaturation for GEO Satellite A. S. Okhitinaa, Ya. V. Mashtakova, *, S. S. Tkacheva, S. A. Shestakova, and M. Yu. Ovchinnikova a
Keldysh Institute of Applied Mathematics, Russian Academy of Sciences, Moscow, 125047 Russia *e-mail: [email protected] Received September 17, 2019; revised September 17, 2019; accepted December 19, 2019
Abstract—The paper considers the problem of the optimal thrusters arrangement aboard a geostationary spacecraft. It is necessary to simultaneously ensure orbit correction and reaction wheels desaturation. A formalization for thrusters optimal arrangement problem is proposed. Examples of the minimal thrusters arrangement are given, taking into account the given limitations and requirements both in the case of regular operation and in the case of a possible failure of one of the thrusters. The influence of possible installation errors and the center of mass displacement is taken into account. DOI: 10.1134/S0010952520050081
INTRODUCTION At present, geostationary satellites are widely used for applied and commercial purposes. Geostationary orbits are one of the most attractive classes of orbits. These are circular orbits located above the Earth’s equator (their inclination is zero). Spacecraft in such orbits revolve around the planet with an angular velocity equal to the angular velocity of the Earth’s rotation around its axis. Thus, geostationary satellites are always above a given point of the equator. This makes it possible, for example, to direct a communication antenna or a satellite television receiving antenna mounted on the Earth to the spacecraft and not to vary its orientation to track the signal transmitted from the satellite, since it is always located in the same place on the celestial sphere. This is also useful for solving the problem of remote sensing, when it is necessary to observe the same surface area for a long time. An example here is the Electro-L satellite [1], which is used for hydrometeorological observations. It should be noted that the geostationary orbit is not stable. In addition to the orbit deployment errors, the evolution of the spacecraft orbit is influenced by a number of external perturbations from the Moon, the Sun, and the noncentrality of the Earth’s gravitational field. Over time, the parameters of the orbit evolve, and it ceases to be geostationary. The orbit evolution is expressed in two main phenomena: the satellite moves along the orbit (along its velocity direction) from its initial position towards one of the stable equilibria [2]; the inclination of the orbit increases (from the initial zero value) with the rate of the order of one degree per year [3].
To maintain the orbit and hold the satellite in an almost predetermined position, thrusters are usually used. They create corrective impulses in the nodes of the orbit. The impulses are applied along North–South direction (in the plane orthogonal to the spacecraft radius-vector, see Fig. 1) to compensate the i
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