A spacecraft solar batteries panels strength calculation
Aeronautical and Space-Rocket Engineering
Design, construction and manufacturing of flying vehicles
Kazan National Research Technical University named after A.N. Tupolev, KNRTU-KAI, 10, Karl Marks str., Kazan, 420111, Russia
The solar battery panels can be divisible by construction into the following types:
– Solar batteries with panels in the form of a frame with the stretched net-like fabric (net-like fabric panel);
– Solar batteries with panels in the form of a frame with orthogonally stretched strings (a string panel);
– Solar batteries with panels in the form of a frame with the stretched flexible film (a film panel);
– Solar batteries in the form of three-layer panels with a honeycomb core (a panel with a honeycomb core);
– Solar batteries with three-layer panels of integral construction (an integral panel).
The structures analysis of various panels reveals that at present all world firms employ generally three-layer panels with honeycomb core.
The structure of such panel consists of carbon fiber-reinforced plastic encasement and a metal honeycomb core.
Pursuing a goal of developing the rigid and light panel, recommendations on selection of carbon fiber-reinforced plastic, honeycomb core, adhesive film and dielectric film are issued based on experiments.
It allowed create lightweight rigid design structure of a solar panel. It was necessary herewith to perform strength, rigidness calculations and vibrations under effect while transportation and operation.
The stress-strain state of panels, forms and natural frequencies were being defined. Calculations were performed by a finite element method in MSC/Nastran.
CQAD4 sheathing element was selected for encasement and honeycomb cores modelling. The CQAD4 element accounts for all internal forcing factors and the encasement geometry, since it perceives membranous, shear, transversal and flexural loadings.
Calculations reveal that tension, occurring in the elements of the offered light-weight structure, have considerable safety margin, and high rigidity at which the maximal shifts do not exceed 0.05 mm, while oscillation frequencies change in within range of 16-91 Hz. The three-layer panel specific mass herewith is only 1.27 kg/m2. The structure opens possibilities for further improvement.
Keywords:three-layer solar battery panel, carbon composite covering, finite element method, panel strength, panel rigidity, panel natural frequency, CQAD4 shell element
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