The Shell-Type Frame for the Small Spacecraft Solar Battery

Aeronautical and Space-Rocket Engineering


Аuthors

Maksimov P. N.1, 2*, Anufrienko V. E.1**, Sin'kovskii F. K.1***, Maksimov V. N.1, 2****

1. Satellite Information Systems, SIS, 62, Lenin str., Zheleznogorsk, Krasnoyarsk Region, 862972, Russia
2. Siberian State University of Science and Technology named after academician M.F. Reshetnev, 31, Krasnoyarsky Rabochy av., Krasnoyarsk, 660014, Russia

*e-mail: 1528d@mail.ru
**e-mail: anufrienkove@iss-reshetnev.ru
***e-mail: sfk@iss-reshetnev.ru. ORCID 0009-0003-5187-0874
****e-mail: 1928d@mail.ru

Abstract

The article presents the development and appraisal of a shell-type load-bearing structure for a solar battery intended for small spacecraft. The basic requirement for this work consisted in creating a frame that would meet the strict rigidity, strength, and weight requirements, as well as be suitable for a large-scale assembly production and ensure efficient heat dissipation.
The growing application of the small spacecraft in modern space missions requires not only the lightweight and compactness of the power supply systems, but their technological adaptability for mass production as well. Analysis of traditional energy sources such as regenerative fuel cells and nuclear generators reveals such limitations as complexity, mass and safety, which makes solar panels the most preferable for the small spacecraft. Besides, a review of the existing solar cell designs, such as rigid (honeycomb panels), semi-rigid (tubular frames with stretched substrates), and flexible, reveals their unsuitability for the solar cells mass production due to their considerable weight, manufacturing complexity, or low efficiency. To fill this gap, a new rigid shell-type frame is being proposed.
The developed frame consists of two polymer composite shells connected by the curved stiffeners. The front shell ensures a flat surface for automatic installation of the photovoltaic modules, and the design makes provision for the through-holes for temperature control, local carbon fiber reinforcements and a special contour for the rigidity enhancing. The inset elements are bring used for integration with the spacecraft. The design philosophy is based on the principle of adaptability, minimizing the number of parts and complexity of assembly.
The finite element model (FEM) in the special software was used for the preliminary structural analysis. Static load tests in the contour and cantilever circuits have confirmed that the design meets the rigidity and strength requirements, and the safety factor exceeds 1.5. Modes analysis revealed that the natural frequency exceeds 30 Hz, which meets the dynamic reliability requirements.
The prototype was fabricated by the manual laying. Its weight of 620 grams (0.87 kg/m2) was 12.7% higher than the computed one. The excess weight over the computed one may be explained by insufficient removal of the excess resin during molding. This is being evidenced by the shell local thickening at the interface of the surfaces. The results of static tests confirmed meeting of the rigidity-and-strength requirements imposed on the frame.
Finally, the developed shell-type frame is a viable solution for the small spacecraft solar panels that meet the key mechanical and dynamic requirements. Its design is inherently suitable for the automated large-scale production with appropriate production capabilities.

Keywords:

solar battery load-bearing structure, shell-type frame, spacecraft mass production, small spacecraft manufacturing

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