Calculation of temporal variation in the transferred power of the loop heat pipe as part of the spaceborne radiation heat exchanger based on temperature sensor measurement data

Abstract

The paper is devoted to a method for determining the power transferred by the loop heat pipe as part of the spaceborne heat exchanger when the transferred power significantly changes as the spacecraft rotates around the Earth. The proposed method allows to calculate excessive heat power removed by the radiation heat exchanger from radio electronic equipment (REE) in space. The parameter behaviour in time shall be known for mathematical modelling of the thermal state of the spacecraft. Readings of temperature sensors installed on structural elements of the spacecraft are used as initial data for the proposed method. The initial data are used to carry out mathematical modelling of the loop heat pipe as part of the spaceborne radiation heat exchanger. The efficiency of the method is proven by means of a thermal model of an active phased antenna array with REE elements, heat insulation and a radiation heat exchanger.