Stress-Strain State Modeling of a Panel from Composite Materials under the Impact of One-Time Sock Loading and Assessment of the Defect Areas Occurrence

Aeronautical and Space-Rocket Engineering


Аuthors

Wai Y. O.*, Mikhailovsky K. V.**

Baumann Moscow State Technical University, 105005, Moscow, 2nd Baumanskaya St., b. 5, c. 1

*e-mail: waiyanoo6977@gmail.com
**e-mail: mikhaylovskiy@bmstu.ru

Abstract

The article considers the stress-strain state modeling of a light sport aircraft wing panel from polymer composite materials (PCM) under the impact of a single shock load caused by a bird strike. The study is aimed at identifying areas in the wing structure where defects and damages occur, depending on the impact speed and the PCM reinforcement scheme. The primary purpose consists in the PCM wing structures impact resistance increasing through the parametric modeling application.
The wing skin panels of the Piper PA-28 aircraft from the carbon fiber and fiberglass with various reinforcement schemes were selected as the subject of research. Numerical modeling of the shock loads was conducted with the ANSYS software suite, applying the Lagrangian method. The two basic reinforcement schemes were considered: [0°, ±45º, 90º]n and [±45º]n.
It was found that carbon fiber panels exhibit higher impact resistance compared to the fiberglass panels. At striking velocities of up to 40 m/s, both panels (carbon fiber and fiberglass) retain structural integrity. However, with the velocity increase up to 50 m/s multiple damage zones and through penetration originate in the fiberglass panels, while the carbon fiber panels sustain impact without through damages.
Special attention is given to the analysis of stress distribution within the PCM layers. It was found that carbon fiber panels with the [±45º]n reinforcement scheme exhibit the highest shock resistance due to the optimal stress distribution within the layered structure. This confirms the expediency of applying this reinforcement scheme for the wing structures.
The obtained results allow the wing structures optimization of the light sport aircraft, enhancing thereby their operational safety. The study confirms that both material and reinforcement scheme selection significantly affects the shock resistance of the structure, which must be considered in the design of aviation structures from the PCM.
Thus, the carbon fiber application with the [±45º]n reinforcement scheme significantly increases resistance of the wing structure to the shock loads caused by the bird strikes while ensuring minimal weight and high strength. This study contributes to the development of more reliable and safer aviation structures.

Keywords:

wing structures strength, shock loading modeling, bird strike simulation, carbon fiber, glass fiber, reinforcement scheme, polymer composite materials

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