Design technique for small spacecraft thermal control system and mathematical models verificatioin based on telelmetry data

DOI: 10.34759/vst-2021-3-113-129

Аuthors

Kaurov I. V., Tkachenko I. S.^*, Salmin V. V.^**

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia

*e-mail: innovatore@mail.ru
**e-mail: sputnik@ssau.ru

Abstract

Thermal mathematical models with distributed and concentrated parameters of the AIST series small spacecraft were developed. Verification of these models was performed based on telemetry data obtained while he spacecraft experimental operation. Verification possibility of theoretical calculations of the supposed small spacecraft temperatures and obtained telemetry parameters allows improving the technique for finding parameters of the thermal control system with improved qualitative indicators. The authors developed the technique for the small spacecraft thermal control system design. Computation of mathematical model of a small spacecraft with distributed parameters was performed with the Simcenter 3D Space Systems Thermal module of the Siemens NX specialized software. Computation of the spacecraft thermal state mathematical model based on differential equations with lumped parameters was performed with MATLAB software package in Simulink environment for the complex technical systems dynamic interdisciplinary modeling.

The developed technique of the thermal mathematical model was applied for developing a computational mathematical model of the thermal state of a prospective small spacecraft for environmental monitoring tasks. Thus, the main objectives of the study are as follows:

– obtaining and analyzing a real picture of the thermal regime of the «AIST» series small spacecraft based on the telemetry data;

– developing thermal mathematical model of a small spacecraft in distributed parameters;

– developing thermal mathematical model of a small spacecraft in lumped parameters;

– verifying computational models by the telemetry data;

– developing design technique for the small spacecraft thermal control system, with appropriate mathematical models application;

– solving partial design problems employing the developed technique.

Keywords:

small spacecraft, leaky spacecraft, thermal modeling, thermal control system

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