A mathematical model is proposed for a heat store with a melting working medium. The store takes the form of parallel plates of a material that undergoes phase transition. Coolant flows between the plates. The function describing the thermophysical properties of the working medium, which changes abruptly on phase transition, is smoothed within a certain temperature range.

Heat Stores with a Melting Working Medium for Spacecraft Thermal Control Systems: Simulation

Heat stores of different design are compared, with a view to identifying the maximum stored energy density and power [1, 2]. The heat store selected has a melting working medium. This design is the most promising for the maintenance of acceptable thermal conditions in spacecraft [3, 4].

Heat Stores with a Melting Working Medium for Spacecraft Thermal Control Systems

An economical method of thermal calculation for heat stores is proposed for engineering practice, on the basis of some theoretical findings regarding regular operation. For purposes of calculation, an additional limitingly thin layer of material is introduced between the contacting phases.

Heat Stores for Thermal Stabilization of Electronic Equipment in Spacecraft

A method is proposed for selecting the design parameters of heat stores used in spacecraft temperature maintenance. The position of the store in the system is chosen. The heat store’s design, geometric dimensions, thermal capacity, and working medium are determined.

Selection of the Design Parameters for Heat Stores in Spacecraft Temperature Maintenance

A thermal model of the International Space Station is proposed and used to calculate the total heat fluxes, by stochastic Monte Carlo modeling. The total heat fluxes consist of solar radiation, the infrared flux reflected from the Earth, and the infrared flux due to radiant heat transfer among the components of the station. On the basis of appropriate boundary conditions, the mean mass temperatures and limiting temperature difference typical of the given orbit are determined.

Heating of Components in the International Space Station

The use of the environmentally friendly solar thermal energy runs into some problems during practical realization of the power systems due to the difficulties of accumulating and storing the produced thermal energy during the lunar night. The paper deals with a solar hot water supply system for a life support system of the lunar bases located at the peaks of eternal light of the North and South Poles of the Moon and able to maintain hot water temperature during a lunar year taking into account the solar eclipses at the Moon. Solar hot water supply system includes a solar collector in the form of an annular cylinder with an axis perpendicular to the surface of the Moon with hydrogen coolant and seasonal storage heater located in lunar soil filled with crushed regolith to maintain hot water temperature during the periods without sun illumination. Design parameters as well as the system efficiency have been evaluated on the basis of the developed mathematical model and computer simulation of dynamic conditions for the system located at the ridge of Peary crater at the North Pole and the ridges of Shackleton and De Gerlache craters and Malapert Mountain at the South Pole of the Moon. It is shown that for the North Pole the water temperature at the lunar base reaches the required level at the end of the first lunation and practically does not change during the solar eclipse due to the presence of heat in the solar system. When the solar system is located in any peak of eternal light at the South Pole, the time it takes for the system to reach the required thermal regime does not exceed 4 lunations, while the required level of hot water is provided throughout the year. It is noted that due to the presence of dark intervals in the southern peaks of eternal light, significantly larger areas of the mid-solar collector and twice the size of the heat accumulator are required compared to the North Pole.

N. S. Kudryavtseva

Papers

The Solar Hot Water Supply System for an Inhabited Base Located at the Moon Poles