Thermal control of a spacecraft: Backward-implicit scheme programming and coating materials analysis

The passive thermal control of a satellite consists establishing the necessary parameters involved in process heat transfer by radiation and conduction order to delimit range temperatures which different components will be exposed. If obtained implies that elements are unable cope with, therefore, an external is demanded. This work deals with programming equilibrium problem taken into consideration backward-implicit scheme. algebraic mathematical approach for steady-state transient analysis implemented Matlab © scripts. In addition, analyzes influence coating materials on benchmark spacecraft reported literature. under scope considers characteristics low Earth Orbit: solar, albedo planetary radiation, coming from other isotherm surfaces same satellite, and, finally, these outer space. procedure based feasible matrix formulation results avoid numerical instabilities prevalent forward-explicit approach, moreover, it enables further parametric sensitivity analysis. Regarding response, most relevant evidence can guarantee desirable temperature spacecraft. We confirm certain material properties like absorptance, emittance its relation (absorption coefficient) essential response system. Nevertheless, do not way. It shown effect lower than absorptance.