Design of Wing Spar Cross Section for Optimum Fatigue Life
Апстракт
Aircraft structure is the most obvious example where functional requirements demand light weight and strong structures. Shape and sizing optimization are being increasingly used nowadays for designing lightweight structural components. The aim of this paper is to present optimization of I-section integral wing spar made of aluminum 2024-T3. The efficient design, based on optimum fatigue life, was achieved using Extended Finite Element Method (XFEM) and its ability to simulate crack growth in complex geometry. The computations were carried out in Morfeo/Crack for Abaqus software which relies on the implementation of XFEM. Shape optimization of the aircraft wing spar beam was conducted by comparing the fatigue crack growth lives for different cross section shapes, but constant cross section area of the spar. The analysis revealed that XFEM is efficient tool for complex three-dimensional configurations optimization where extended fatigue life is one of the most important objectives.
Кључне речи:
optimization / fatigue life / Extended Finite Element Method / aircraft structureИзвор:
Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity, 2018, 13, 444-449Издавач:
- Elsevier Science Bv, Amsterdam
DOI: 10.1016/j.prostr.2018.12.074
ISSN: 2452-3216
WoS: 000459860900073
Scopus: 2-s2.0-85064705712
Колекције
Институција/група
Mašinski fakultetTY - CONF AU - Eldwaib, Khalid AU - Grbović, Aleksandar AU - Kastratović, Gordana AU - Aldarwish, Mustafa PY - 2018 UR - https://machinery.mas.bg.ac.rs/handle/123456789/2814 AB - Aircraft structure is the most obvious example where functional requirements demand light weight and strong structures. Shape and sizing optimization are being increasingly used nowadays for designing lightweight structural components. The aim of this paper is to present optimization of I-section integral wing spar made of aluminum 2024-T3. The efficient design, based on optimum fatigue life, was achieved using Extended Finite Element Method (XFEM) and its ability to simulate crack growth in complex geometry. The computations were carried out in Morfeo/Crack for Abaqus software which relies on the implementation of XFEM. Shape optimization of the aircraft wing spar beam was conducted by comparing the fatigue crack growth lives for different cross section shapes, but constant cross section area of the spar. The analysis revealed that XFEM is efficient tool for complex three-dimensional configurations optimization where extended fatigue life is one of the most important objectives. PB - Elsevier Science Bv, Amsterdam C3 - Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity T1 - Design of Wing Spar Cross Section for Optimum Fatigue Life EP - 449 SP - 444 VL - 13 DO - 10.1016/j.prostr.2018.12.074 ER -
@conference{ author = "Eldwaib, Khalid and Grbović, Aleksandar and Kastratović, Gordana and Aldarwish, Mustafa", year = "2018", abstract = "Aircraft structure is the most obvious example where functional requirements demand light weight and strong structures. Shape and sizing optimization are being increasingly used nowadays for designing lightweight structural components. The aim of this paper is to present optimization of I-section integral wing spar made of aluminum 2024-T3. The efficient design, based on optimum fatigue life, was achieved using Extended Finite Element Method (XFEM) and its ability to simulate crack growth in complex geometry. The computations were carried out in Morfeo/Crack for Abaqus software which relies on the implementation of XFEM. Shape optimization of the aircraft wing spar beam was conducted by comparing the fatigue crack growth lives for different cross section shapes, but constant cross section area of the spar. The analysis revealed that XFEM is efficient tool for complex three-dimensional configurations optimization where extended fatigue life is one of the most important objectives.", publisher = "Elsevier Science Bv, Amsterdam", journal = "Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity", title = "Design of Wing Spar Cross Section for Optimum Fatigue Life", pages = "449-444", volume = "13", doi = "10.1016/j.prostr.2018.12.074" }
Eldwaib, K., Grbović, A., Kastratović, G.,& Aldarwish, M.. (2018). Design of Wing Spar Cross Section for Optimum Fatigue Life. in Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity Elsevier Science Bv, Amsterdam., 13, 444-449. https://doi.org/10.1016/j.prostr.2018.12.074
Eldwaib K, Grbović A, Kastratović G, Aldarwish M. Design of Wing Spar Cross Section for Optimum Fatigue Life. in Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity. 2018;13:444-449. doi:10.1016/j.prostr.2018.12.074 .
Eldwaib, Khalid, Grbović, Aleksandar, Kastratović, Gordana, Aldarwish, Mustafa, "Design of Wing Spar Cross Section for Optimum Fatigue Life" in Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity, 13 (2018):444-449, https://doi.org/10.1016/j.prostr.2018.12.074 . .