Abstract
Objective: The aim of this article is to solve the problem of wing spar flexibility of an aluminium drone aircraft. A 200 × 30 [mm × mm] aluminium sample weighing 32 g was collected corresponding to a density of 0.53 g/cm3, a bending load of 0.77 [kN] and a deflection of 45.54 mm. The goal is to increase flexion resistance and lightness. Methods: The following procedure was used to prepare the composite: a mold made up of two glass plates 250 mm long and 50 mm wide, gel-coated to prevent sticking. The mold was placed in a bag using vacuum bag technology by means of a refrigerator compressor. The bag was then heated at 80 °C for seven hours to prepare composites of acceptable quality and viscosity avoiding air bubbles and ensuring desired thickness. The first sample was prepared by inserting aluminium powder between four layers of glass fiber. In the second sample, the inserted layer was replaced by date pit powder. The third sample was prepared by placing four layers of glass fiber and two layers of carbon fiber in the lower layer and the upper layer. It was observed that aluminium powder inclusion resulted in better mechanical properties in comparison to date pit powder. Findings: However, the mechanical characteristics of the third sample were much better than those of the other samples. Based on these observations, the first and third samples were mixed to make the fourth sample in which four layers of glass fiber between each layer were used, placing the aluminium powder plus two layers of carbon fiber in the lower and upper layers with the aim of achieving the desired mechanical properties. The latter sample exhibited high strength and better curvature, high rigidity and corrosion resistance with the possibility of creating structures that are more integrated. These properties make the aluminium powder –carbon fiber based composite suitable for a drone aircraft wing spar. The obtained composite material prepared from glass fiber, aluminium powder, carbon fiber composed of four layers of glass fiber and aluminium powder between each layer and carbon fiber in the bottom layer and top layer exhibited has high strength, better bending, high stiffness and corrosion resistance with the possibility of creating more integrated structures. The prepared sample may outstand aluminium -based aircraft wing spar. Keywords Wing spar, bending, composite materials, aluminiumcarbon fiber
Highlights
Due to globalization and military needs, the aircraft industry has become very crucial and useful in all fields and aspects of modern life
Three-point bending tests were performed on the prepared specimens according to NFT57-104 and105 standard procedures [25] as depicted in (Figure 14 ). (L=200 mm, b=30 mm, h=2mm)
This work studied the mechanical properties of four different composites for their suitability for drone aircraft wing spar applications
Summary
Due to globalization and military needs, the aircraft industry has become very crucial and useful in all fields and aspects of modern life. Composite materials are mainly used for industrial purposes for diverse reasons [3]. These include an excellent mass/rigidity/resistance ratio in comparison with metallic materials, a design of appropriate materials in solicitation axes in order to make additional weight gains [4] and increased fatigue resistance in comparison with metallic materials [5]. Knowledge of the mechanical properties and structure of a composite makes it possible to understand, even predict its behaviour in service. The understanding of the mechanical characteristics of a composite material and its structures open doors for the comprehension and prediction of its behaviour in service
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