Increasing the strength of the composite material of the aircraft

Abstract

 Metals have been widely used as the preferred material for aircraft construction since the 1930s. The base metals used in the aerospace industry range from alloyed and heat-treated aluminum to titanium, magnesium and superalloys, the latter being designed for special use. However, changes in the design of the aircraft, especially with regard to the materials used, began in the 1970s, when composite materials were introduced into commercial aircraft. One of the driving forces behind the increased use of composite materials is their ability to create relatively lightweight components and aerodynamically engineered structures that reduce fuel costs while maintaining high strength and performance. Safety is an mportant factor in aviation and therefore has a decisive influence on the choice of materials. Therefore, when choosing materials for the aircraft structure, it is necessary to take into account design parameters such as weight and strength, as well as safety factors such as failure modes and performance. The aerospace industry shows that when switching to composite materials, it is very important to understand how relatively new materials react to failures and damage. This article uses an example of an airplane wing design to demonstrate the capabilities of modeling composite materials in a SolidWorks environment. The mechanical properties of composite materials used in aircraft and the process of modeling such structures are written in SolidWorks. The purpose of this study is to simulate flow calculations and reliability analysis in SolidWorks Flow Simulation. For each analyzed load type, different values of displacement, voltage and safety factor were obtained for each analyzed load type.