Designing frames of integrated cfrp solar panels for spacecraft

This article deals with the problem of ensuring the competitiveness of space systems by increasing the energy and mass efficiency of solar panels. It provides a review of modern designs of the solar panel frames intended for use in spacecraft, and a choice of design and technological solutions for the creation of integrated structures of the solar panel frames with a low specific weight. A model of a composite integrated frame is developed that ensures the bearing capacity of the solar panel at a given static gravitational load at the time of launch and in operation. The results of the selection of rational parameters for the elements of the integrated solar panel frame are given. The results obtained in the framework of the adopted assumptions and the initial characteristics of the polymer composite materials warrant the possibility of realization of the specific gravity in the range of 0.55–0.65 kg/m², with a regulated load bearing capacity and stiffness, thereby complying with the world trends for objects of this class. Using the proposed design, it is possible to place lens concentrators over the photovoltaic converters installed on the frame, which in turn can significantly increase the specific power of the solar cell.

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