Construction of high-temperature solar power plants for small-size spacecrafts requires development of concentrating systems having the size which may significantly exceed overall dimensions of both spacecraft itself and its transport compartment under the carrier rocket fairing. One of the perspective ways for creating the systems of this type is the application of ultralight inflatable rigidizable solar energy mirror concentrating systems (MCS). Experimental definition of characteristics of such MCSs requires complicated and expensive experiments. Therefore, the development of mathematical models which make it possible to calculate the specifications considering the effect of operating conditions, design features, deformations and different surface defects, is of special interest. This paper provides brief analysis of structural features of large-scale inflatable rigidizable MCSs as applied to small-size spacecrafts, and a statistical mathematical model which enables their basic radiation and energetic characteristics considering the effect of the factors mentioned above.
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