Two-dimensional thermal model of the thermal control system for nonhermetic formation spacecraft

Based on the proposed computational model including a two-dimensional system of equations of thermal balance characteristic of the surface of thermal control system of nonhermetic formation spacecraft the algorithm and the cal- culation program of the temperature control system are developed. It allows to calculate integrated thermal parameters and conduct simulations of the system response. We consider the case of a two-dimensional problem, when arising tem- perature gradients in the transverse direction (Y-axis) and longitudinal direction (X-axis) is taken into account, while the conductive heat transfer inside the skin along the X-axis of the profile of the liquid circuit of the thermal control system is neglected. In this case the transverse gradient (along the Y-axis) is formed by Fourier heat conduction equa- tions through characteristic surfaces, while the longitudinal gradient (along the X-axis) is determined by the heat and mass transfer processes by the refrigerant flow in the liquid ring circuit. The number of docking thermal balances (equations) and, accordingly, the determined temperatures are correlated by the constructive elements of the spacecraft thermal control system: radiation surfaces (N - North, S - South); structural honeycomb panels; heat pipes; liquid circuit.