Calculation of Radiation Characteristics of a Circular Waveguide Covered with Thermal Protection and Plasma Layer

Abstract

A mathematical model of an aerospace antenna of a space vehicle on the descending trajectory taking into account thermal protection and plasma layer has been developed. The results of numerical calculation of losses of electromagnetic energy in the heated thermal protection of a circular waveguide and plasma layer are presented. An algorithm for calculating the mathematical model has been suggested. The calculation has been performed to determine the influence of a change in thickness and electric parameters of the thermal protection and plasma layer on the radiation pattern and efficiency.