Computational modeling of the curing of a frame of an inflatable satellite antenna in near-earth orbit

Temperature analysis of a new technological process, curing of prepregs in near-earth orbit, is performed via computational modeling. The problem arose in connection with the currently discussed possibility of using inflatable antennas for small space satellites. Inflatable antennas have a number of advantages over classic extendable metal antennas. However, in order to ensure the continuous operation of inflatable antennas, it is necessary that they acquire rigidity over time and cease to depend on the pressure of air in them. This can be achieved using a frame made of an orbital-curable prepreg. This idea requires experimental justification and analysis by means of computational modeling. In this work, only one of the aspects (temperature effect) of the in-orbit curing technological process is considered. The creation of special equipment for heating prepregs in the satellite body is undesirable because it will increase weight and sizes of a satellite. However, the natural heating of structural elements in space can be due to the radiation emitted from the Sun and the Earth. Numerical experiments demonstrate that the required curing temperature can be achieved in the case when, instead of a simple prepreg frame, use is made of the frame on which a thin layer of copper is deposited. Temperature distributions in the structure during its rotation are examined. Analysis of the results yields time intervals at which the antenna orientation with respect to the solar flux direction should be changed in order to obtain the required temperatures, striving to achieve curing of all elements of the frame in a small number of revolutions around the Earth, that is, as long as a high gas pressure remains in the inflatable antenna.