- Title
- Multi-Criteria Decision-Making based Materials Selection of a Lightweight Aircraft Wing Spar and Rib
- Creator
- Saeed, Maryam; Haq, Rana Sami Ul; Ahmed, Sohail; Siddiqui, Faisal; Asim, Anas; Yi, Jiabao
- Relation
- 4th International Conference on Digital Futures and Transformative Technologies, ICoDT2 2024. Proceedings of the 4th International Conference on Digital Futures and Transformative Technologies, ICoDT2 2024 (Islamabad, Pakistan 22-23 October, 2024) p. 1-13
- Publisher Link
- http://dx.doi.org/10.1109/ICoDT262145.2024.10740214
- Publisher
- Institute of Electrical and Electronics Engineers (IEEE)
- Resource Type
- conference paper
- Date
- 2024
- Description
- A real-time problem of a failing wing, owing to the low yield strength of the aluminum alloy 7050-T7451, is considered for an optimized material selection. Thus, an expert system for material selection is developed in this research work to find suitable materials for wing members (e.g., spar, rib). First, the right set of critical design criteria are determined, and weights are assigned using the Analytical Hierarchy Process (AHP) and Modified Digital Logic (MDL) methods. Then, the preliminary screened-out candidates from Ashby's charts are ranked using seven Multi-Criteria Decision Making (MCDM) techniques, i.e., Preference Ranking Organization Method for Enrichment and Evaluation (PROMETHEE II), Evaluation of Mixed Data (EVAMIX), Interactive and multiple attribute decision making (TODIM), Technique for Order of Preference by Similarity to Ideal Solution (TOPSIS), Multi-criteria optimization and compromise solution (VIKOR), Complex Proportional Assessment (COPRAS), and Weighted Property Method (WPM) with Z-transformation normalization. Finally, the linear static structural analysis is carried out on the top-ranked alternatives of spar (7068-T6511, 7255-T7751, 7055-T76511, and 7349-T6511), keeping the rib material (7050-T7451) unchanged under the specified loading conditions to obtain the deformation, von Mises stress, and factor of safety. The results show that the top-ranked alternatives can be used interchangeably for the spar application. Similarly, rib material optimized for wing loading conditions and cultural constraints is selected using MCDM methods. Next, for the wing to operate within safe operational limits, both spar and rib are analyzed using the best-performing alternative, i.e., 7068-T6511 resulting in Factor of Safety (FoS) within the acceptable range (>1.50).
- Subject
- material selection; Multi-Criteria Decision Making (MCDM); lightweight aircraft; structural analysis; aluminium alloy; wing spar
- Identifier
- http://hdl.handle.net/1959.13/1518638
- Identifier
- uon:57355
- Identifier
- ISBN:9798350391862
- Language
- eng
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