Optimal structure of multi-layer wing console of unmanned aerial vehidle with experimental validation

Aeronautical and Space-Rocket Engineering

Design, construction and manufacturing of flying vehicles


DOI: 10.34759/vst-2020-1-65-75

Аuthors

Bokhoeva L. A.1*, Baldanov A. B.1**, Chermoshentseva A. S.2***

1. East Siberia State University of Technology and Management, 40v, Klyuchevskaya str, Ulan-Ude, Republic of Buryatia, 670013, Russia
2. Bauman Moscow State Technical University, MSTU, 5, bldg. 1, 2-nd Baumanskaya str., Moscow, 105005, Russia

*e-mail: bohoeva@yandex.ru
**e-mail: aldarbaldanov@gmail.com
***e-mail: asch-13@ya.ru

Abstract

The article explores stress-strain state of a composite layered wing console of an unmanned aerial vehicle (UAV). An optimal structure of the multilayer skin, ensuring maximum strength and stiffness at the specified loads was determined with the ANSYS system. The wing structure consists of two complete and two incomplete layers. Automated procedure for fiber laying angle selection in a layer was developed. Seventeen options of fiber laying angle were obtained, out of which three options of optimal reinforcing were selected. The second supplementary layer was added over the entire wing surface for deformation reduction. Thirty three options of fibers laying were considered while computing the wing model of two layers. When conputing three layers, forty seven options of fibers laying in a layer were considered. Sixty four options of fibers laying were regarded while computing a wing of two complete and two incomplete layers. According to the performed calculations, a four layer wing console was produced from layered fiberglass. It was produced by the cold forming method. Workshop drawings of tooling were developed. New tooling from phenol-impregnated modified wood was obtained for the hollow wing console fabrication, for which a Patent No 19273 was received. The weight of the hollow console is 1.46 kg, which is 3% greater than that for the computational model. The designed and fabricated wing console of the two complete and two incomplete layers weight is 43% less than that of the console of the two complete layers. Fabrication of the designed console requires 25-30% less material. The presented approach can be widely employed while structural elements and products from composite materials design and fabrication.

Keywords:

optimal wing console, strength, stiffness, multilayer composite structures, fiber laying angle, tooling, cold forming method

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