It is of great importance for the airlines to cut emissions both for better “Environmental Social Governance” metrics which are going to be prevalent in the near future due to certain limitations placed in by certain governmental bodies around the world, and for better profitability since having less emissions is relatively proportional with using less fuel, hence better operating margins for aircrafts. Due to these reasons, a heavy polluter industry such as aviation shall adopt soon, keep up with the competition, and to comply with the newer regulations. One of the possible ways to achieve this is mass reduction. To reduce mass in an aircraft, one can remove some fasteners deemed not necessary, given that the structural performance is kept same via other ways (such as an introduction of a superior material usage), or a new material can be used altogether. In an aircraft, one can infer that most of the mass is located throughout the fuselage, specifically frames that are longitudinally placed within it and connected via a set of stringers. This paper will investigate ways to deal with, and improve the situation using mechanical analysis tools, whilst keeping the structure relatively same to alleviate potential manufacturing challenges that might arise. Accordingly, a select few aerospace materials such as Al-7075, Al-2024, and a honeycomb composite structure are subjected to a series of tension tests, and findings are reported. Using the results obtained from these laboratory tests, structural improvements have been observed. "This study was inspired by the first author's master's thesis. ORCID NO: 0009-0000-1814-8845"
Anahtar Kelimeler: Aircraft Frame, FED, Strength, Composite
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