METHOD OF ESTABLISHING OPTIMUM VALUE OF EQUIVALENT ISOTROPICALLY RADIATED POWER OF SPACECRAFT TRANSMITTING SYSTEM ON LOW CIRCULAR ORBIT FOR COMMUNICATION WITH RETRANSMITTER IN HIGH-ALTITUDE CIRCULAR ORBIT Russian patent published in 2021 - IPC H04B7/185 

FIELD: astronautics.

SUBSTANCE: invention relates to space systems for relaying information between low-Earth orbital spacecrafts (SC) and control centers and receiving messages using high-orbit, mainly geostationary satellites-retransmitters (SR). For this purpose, the equivalent isotropically radiated power of the spacecraft is represented by a function of the angle of deflection of the line of sight "spacecraft - satellite-transponder" from the direction "satellite-retransmitter - center of the Earth" δ, when a receiving antenna with a wide fixed beam is used on a relay satellite, the values of the length of the inter-satellite line and the gain of the receiving antenna of the retransmission satellite are calculated for the value of the angle δ, which satisfies the condition d [D²(δ)/F2(δ)]/dδ = 0, where D (δ) is the length of the "spacecraft - satellite-retransmitter" communication line, defined as D(δ) = R_SRcosδ + (R2_SC - R2_SR sin2δ)0.5, R_SR and R_SC are orbit radii of satellite retransmitter and spacecraft respectively, F²(δ) is a function of directivity of receiving antenna of retransmission satellite.

EFFECT: technical result consists in developing a method which enables to establish minimum required parameters of low-orbit SC transmission system due to consideration of features of information transfer via inter-satellite line to high-orbit SR equipped with a receiving antenna.

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