PLANNING MANEUVERS FOR STABILIZATION THE FLIGHT ALTITUDE OF A RADAR SATELLITE USING AN ELECTRIC PROPULSION SYSTEM
Abstract
The article is devoted to the development of a method for planning the activation of an electric propulsion system to provide the stabilization of the flight altitude of a radar satellite in the ascending node of the orbit, taking into account the limitations of the power supply system. A method for stabilization the satellite trajectory to the nominal flight altitude has been developed. It is based on the solution of the variational problem of finding the optimal combination of an electric propulsion system burning time, the orientation of the thrust vector, and the orbital argument of the latitude of the ignition point. A mathematical model of the satellite's motion, as a point of variable mass, under the influence of the thrust forces of an electric propulsion system, the Earth's gravity and the aerodynamic drag of the Earth's atmosphere has been developed. The control program and its functionalities for the electric propulsion system have been determined. It is shown that taking into account the limitation on the burning time of the electric propulsion system leads to the need of distribution of the flight altitude stabilization maneuver into several ignitions, between which there are sections of the satellite battery charge. It is proposed for all activations of the flight altitude stabilization maneuver, except for the last one, to represent the search for parameters of the control program as a problem of maximum compensation for orbital deviation with minimal consumption of the working substance and a limitation on the electric propulsion system burning time. For the last activation - to represent it as problem of providing a given level of deviation of the orbit altitude while minimizing the consumption of the working substance. Computer simulation was carried out, which confirmed the efficiency of the proposed method. The dependences of the flow working substance mass consumption and the average number of maneuvers required to stabilize the altitude of the orbit of a satellite with a 210-5 thrust-to-weight ratio and average ballistic coefficient of 0.01 m2/kg on the altitude of the sun-synchronous orbit are determined.
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