METHOD OF ESTABLISHING OPTIMUM VALUE OF EQUIVALENT ISOTROPICALLY EMITTED POWER OF TRANSMITTING SYSTEM OF SPACECRAFT ON LOW CIRCULAR ORBIT FOR COMMUNICATION WITH RETRANSMISSION SATELLITE ON HIGH CIRCULAR ORBIT EQUIPPED WITH RECEIVING ANTENNA WITH NARROW CONTROLLED BEAM

摘要

FIELD: astronautics.SUBSTANCE: invention relates to space systems for relaying information between low-orbiting spacecrafts and control centers and receiving messages using high-orbit, mainly geostationary satellites-retransmitters. In order to achieve the said objective, the values of the length of the inter-satellite line and the noise temperature of the receiving system of the retransmission satellite are calculated for the threshold value of the deflection angle of the line of sight "spacecraft - satellite-retransmitter" from the direction "SR - center of the Earth", where Ris radius of Earth, Ris the radius of the orbit SR, h is the minimum allowable height of the passage of the intersatellite line above the Earth's surface.EFFECT: technical result consists in developing a method which enables to establish minimum required parameters of a low-orbital spacecraft transmitting system, represented in the form of equivalent isotropically emitted power, by taking into account features of transmitting information over an inter-satellite line to a high-orbit relay satellite.1 cl, 4 dwg, 1 tbl