METHOD OF DETERMINING ORBIT PARAMETERS OF AN ARTIFICIAL EARTH SATELLITE USING RECEIVING-TRANSMITTING SUPPORTING REFERENCE STATIONS

摘要

FIELD: cosmonautics.;SUBSTANCE: invention relates to the field of cosmonautics, namely to technique of performing trajectory measurements and determining the parameters of the orbit of an artificial Earth satellite (AES), and can be used on ground and airborne flight control complexes to accurately determine the current parameters of satellite motion. In order to achieve technical result, ground radio station (GRS) is used in receiving-transmitting mode, which is located at position with known coordinates of receiving-transmitting supporting reference stations (RTSRS) at positions with known coordinates. Method is based on radiation of radio signals of GRS and M RTSRS and subsequent reception of these test radio signals after retransmission of AES with the help of GRS and M RTSRS. In the GRS and each of M RTSRS, the inclined ranges from the artificial Earth satellite to the GRS and M RTSRS are measured, as well as radial velocities of the artificial Earth satellite relative to the GRS and M RTSRS. Parameters of the artificial satellite orbit are taken to be a set of coordinates of the artificial Earth satellite and orthogonal components of its velocity vector at time t₀, calculated in GRS based on measured distances, as well as radial velocities.;EFFECT: high accuracy of determining parameters of a satellite orbit.;1 cl, 5 dwg