Abstract
Summary A celestial body influence on almost parabolic satellite orbit is analysed. It is important for gravitational field research using satellite geodesy dynamic method. New formulas of first-degree celestial body disturbances for determining almost parabolic satellite orbit elements are derived. Series for disturbances absolutely converge at different values of satellite orbit eccentricity. At a higher eccentricity convergence velocity is increasing. Formulas could be used for the Moon, the Sun and other celestial bodies' effect on satellite orbit determination. Formulas could be used for part of the orbit closer to perigee. An algorithm created will help using satellites moving in almost parabolic orbits for solution of satellite geodesy tasks. Usage of satellites moving in almost parabolic orbits will result in collection of more information on the Earth's gravitational field and better determining the gravitational field parameters.
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