Верификация тепловой математической модели с сосредоточенными параметрами малого космического аппарата серии «АИСТ» на основе телеметрических данных, полученных в ходе его экспериментальной эксплуатации

Abstract

The purpose of the study was to model a small spacecraft of the AIST series and verify this thermal mathematical lumped-parameter model using differential equations and relying on telemetry data obtained during the experimental operation of the spacecraft. Thermal lumped-parameter models are widely spread in designing small-sized onboard equipment for small spacecraft. The model calculation was done by Simulink, the MATLAB-based graphical programming environment for modeling multidomain dynamical systems. We developed a system of equations, consisting of equations for each zone from the outer and inner sides, as well as the equations for scientific equipment. The small spacecraft design is based on three-layer honeycomb panels with heat pipes. Photocells are installed on the outer sides of the panels of the spacecraft, thus making a significant contribution to its thermal state.