TY  - JOUR
AU  - Grbović, Aleksandar
AU  - Kastratović, Gordana
AU  - Sedmak, Aleksandar
AU  - Eldwaib, Khalid
AU  - Kirin, Snežana
PY  - 2019
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/3107
AB  - Shape optimisation is a nowadays-standard requirement in the design of lightweight structural components. In this paper, optimisation of I-beam cross-section of integral aluminium 2024-T3 wing spar is presented, taking the maximum fatigue life as the criterion. Toward this aim, the extended finite element method (XFEM) was used to simulate crack growth in complex I-beam geometry. The computations were carried out using Morfeo/Crack add-on based on XFEM implementation in Abaqus software. Fatigue lives of wing spars with different sizes of cross section but constant area were compared. Conducted analysis has shown that XFEM seems to be efficient tool for complex three-dimensional configurations optimisation.
PB  - Elsevier Sci Ltd, Oxford
T2  - International Journal of Fatigue
T1  - Determination of optimum wing spar cross section for maximum fatigue life
EP  - 311
SP  - 305
VL  - 127
DO  - 10.1016/j.ijfatigue.2019.06.019
ER  - 

@article{
author = "Grbović, Aleksandar and Kastratović, Gordana and Sedmak, Aleksandar and Eldwaib, Khalid and Kirin, Snežana",
year = "2019",
abstract = "Shape optimisation is a nowadays-standard requirement in the design of lightweight structural components. In this paper, optimisation of I-beam cross-section of integral aluminium 2024-T3 wing spar is presented, taking the maximum fatigue life as the criterion. Toward this aim, the extended finite element method (XFEM) was used to simulate crack growth in complex I-beam geometry. The computations were carried out using Morfeo/Crack add-on based on XFEM implementation in Abaqus software. Fatigue lives of wing spars with different sizes of cross section but constant area were compared. Conducted analysis has shown that XFEM seems to be efficient tool for complex three-dimensional configurations optimisation.",
publisher = "Elsevier Sci Ltd, Oxford",
journal = "International Journal of Fatigue",
title = "Determination of optimum wing spar cross section for maximum fatigue life",
pages = "311-305",
volume = "127",
doi = "10.1016/j.ijfatigue.2019.06.019"
}

Grbović, A., Kastratović, G., Sedmak, A., Eldwaib, K.,& Kirin, S.. (2019). Determination of optimum wing spar cross section for maximum fatigue life. in International Journal of Fatigue
Elsevier Sci Ltd, Oxford., 127, 305-311.
https://doi.org/10.1016/j.ijfatigue.2019.06.019

Grbović A, Kastratović G, Sedmak A, Eldwaib K, Kirin S. Determination of optimum wing spar cross section for maximum fatigue life. in International Journal of Fatigue. 2019;127:305-311.
doi:10.1016/j.ijfatigue.2019.06.019 .

Grbović, Aleksandar, Kastratović, Gordana, Sedmak, Aleksandar, Eldwaib, Khalid, Kirin, Snežana, "Determination of optimum wing spar cross section for maximum fatigue life" in International Journal of Fatigue, 127 (2019):305-311,
https://doi.org/10.1016/j.ijfatigue.2019.06.019 . .

TY  - 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 . .

TY  - JOUR
AU  - Eldwaib, Khalid
AU  - Grbović, Aleksandar
AU  - Sedmak, Aleksandar
AU  - Kastratović, Gordana
AU  - Petrašinović, Danilo
AU  - Sedmak, Simon
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2897
AB  - This paper presents the application of the extended finite element method (XFEM) in crack propagation simulation on the integral wing spar that should replace existing differential spar of the light aircraft UTVA 75. Numerical model of integral spar was developed in software Abaqus. Stress intensity factors (SIFs) were calculated using add-in Morfeo/Crack for Abaqus and obtained number of cycles that would propagate crack to certain length was compared to the experimentally obtained number of cycles for differential spar. Numerical analysis showed that integral spar with the same dimensions as differential spar has significant increase in fatigue life. Analysis that was carried out showed that XFEM could be efficient and cost beneficial tool for simulation of crack propagation in the 3D structures (such as wing spar) and that it should be used in the future for fatigue analysis of newly designed structures in all phases of development and production.
PB  - Univ Osijek, Tech Fac, Slavonski Brod
T2  - Tehnički vjesnik
T1  - Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM
EP  - 1842
IS  - 6
SP  - 1837
VL  - 25
DO  - 10.17559/TV-20171007105350
ER  - 

@article{
author = "Eldwaib, Khalid and Grbović, Aleksandar and Sedmak, Aleksandar and Kastratović, Gordana and Petrašinović, Danilo and Sedmak, Simon",
year = "2018",
abstract = "This paper presents the application of the extended finite element method (XFEM) in crack propagation simulation on the integral wing spar that should replace existing differential spar of the light aircraft UTVA 75. Numerical model of integral spar was developed in software Abaqus. Stress intensity factors (SIFs) were calculated using add-in Morfeo/Crack for Abaqus and obtained number of cycles that would propagate crack to certain length was compared to the experimentally obtained number of cycles for differential spar. Numerical analysis showed that integral spar with the same dimensions as differential spar has significant increase in fatigue life. Analysis that was carried out showed that XFEM could be efficient and cost beneficial tool for simulation of crack propagation in the 3D structures (such as wing spar) and that it should be used in the future for fatigue analysis of newly designed structures in all phases of development and production.",
publisher = "Univ Osijek, Tech Fac, Slavonski Brod",
journal = "Tehnički vjesnik",
title = "Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM",
pages = "1842-1837",
number = "6",
volume = "25",
doi = "10.17559/TV-20171007105350"
}

Eldwaib, K., Grbović, A., Sedmak, A., Kastratović, G., Petrašinović, D.,& Sedmak, S.. (2018). Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM. in Tehnički vjesnik
Univ Osijek, Tech Fac, Slavonski Brod., 25(6), 1837-1842.
https://doi.org/10.17559/TV-20171007105350

Eldwaib K, Grbović A, Sedmak A, Kastratović G, Petrašinović D, Sedmak S. Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM. in Tehnički vjesnik. 2018;25(6):1837-1842.
doi:10.17559/TV-20171007105350 .

Eldwaib, Khalid, Grbović, Aleksandar, Sedmak, Aleksandar, Kastratović, Gordana, Petrašinović, Danilo, Sedmak, Simon, "Fatigue Life Estimation of Damaged Integral Wing Spar Using XFEM" in Tehnički vjesnik, 25, no. 6 (2018):1837-1842,
https://doi.org/10.17559/TV-20171007105350 . .

TY  - CONF
AU  - Kastratović, Gordana
AU  - Aldarwish, Mustafa
AU  - Grbović, Aleksandar
AU  - Vidanović, Nenad
AU  - Eldwaib, Khalid
PY  - 2018
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2824
AB  - The aim of this paper is to explore and to demonstrate the capacity, performances and difficulties of stress intensity factors (SIFs) calculations in a case of multiple cracks on curved panels analyzed by means of different computational methods. So-called bulging effect, which is occurring in cracked curved panels, increases the effective stress-intensity factor, making the SIFs assessment in case of multiple cracks more challenging. Here, the stress intensity factors are considered by using two different computational methods: extended finite element method (XFEM) and the approximate method based on superposition, which has been adjusted for curved panel application. The SIFs determination was carried out for aircraft fuselage model: unstiffened panel with three cracked fastener holes, for four different curvature diameters, subjected to uniform internal pressurization. The comparison of the results showed that conducted analyses delivered the data which can be useful in evaluation of crack-growth rate, residual strength and fatigue life of curved aircraft structures with multi-site damage.
PB  - Elsevier Science Bv, Amsterdam
C3  - Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity
T1  - Stress intensity factor for multiple cracks on curved panels
EP  - 474
SP  - 469
VL  - 13
DO  - 10.1016/j.prostr.2018.12.078
ER  - 

@conference{
author = "Kastratović, Gordana and Aldarwish, Mustafa and Grbović, Aleksandar and Vidanović, Nenad and Eldwaib, Khalid",
year = "2018",
abstract = "The aim of this paper is to explore and to demonstrate the capacity, performances and difficulties of stress intensity factors (SIFs) calculations in a case of multiple cracks on curved panels analyzed by means of different computational methods. So-called bulging effect, which is occurring in cracked curved panels, increases the effective stress-intensity factor, making the SIFs assessment in case of multiple cracks more challenging. Here, the stress intensity factors are considered by using two different computational methods: extended finite element method (XFEM) and the approximate method based on superposition, which has been adjusted for curved panel application. The SIFs determination was carried out for aircraft fuselage model: unstiffened panel with three cracked fastener holes, for four different curvature diameters, subjected to uniform internal pressurization. The comparison of the results showed that conducted analyses delivered the data which can be useful in evaluation of crack-growth rate, residual strength and fatigue life of curved aircraft structures with multi-site damage.",
publisher = "Elsevier Science Bv, Amsterdam",
journal = "Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity",
title = "Stress intensity factor for multiple cracks on curved panels",
pages = "474-469",
volume = "13",
doi = "10.1016/j.prostr.2018.12.078"
}

Kastratović, G., Aldarwish, M., Grbović, A., Vidanović, N.,& Eldwaib, K.. (2018). Stress intensity factor for multiple cracks on curved panels. in Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity
Elsevier Science Bv, Amsterdam., 13, 469-474.
https://doi.org/10.1016/j.prostr.2018.12.078

Kastratović G, Aldarwish M, Grbović A, Vidanović N, Eldwaib K. Stress intensity factor for multiple cracks on curved panels. in Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity. 2018;13:469-474.
doi:10.1016/j.prostr.2018.12.078 .

Kastratović, Gordana, Aldarwish, Mustafa, Grbović, Aleksandar, Vidanović, Nenad, Eldwaib, Khalid, "Stress intensity factor for multiple cracks on curved panels" in Procedia Structural Integrity - ECF22 - Loading and environmental effects on structural integrity, 13 (2018):469-474,
https://doi.org/10.1016/j.prostr.2018.12.078 . .

TY  - JOUR
AU  - Eldwaib, Khalid
AU  - Grbović, Aleksandar
AU  - Kastratović, Gordana
AU  - Radu, Dorin
AU  - Sedmak, Simon
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2728
AB  - In this study a central crack tension (CCT) specimen is chosen for analysis to demonstrate the capability and reliability of the extended finite element method (XFEM) in predicting the crack propagation trajectory and evaluating stress intensity factors (SIFs). This specimen is frequently used in fatigue tests for studying various effects on fatigue crack propagation and for obtaining crack growth properties of a material. The XFEM obtained SIFs solutions are compared with several well-known solutions from literature. Evaluation of fatigue life of the CCT specimen is also carried out and compared with the obtained by NASGRO.
PB  - Institut za ispitivanje materijala, Beograd
T2  - Structural Integrity and Life
T1  - Fatigue life estimation of cct specimen using xfem
EP  - 156
IS  - 2
SP  - 151
VL  - 17
UR  - https://hdl.handle.net/21.15107/rcub_machinery_2728
ER  - 

@article{
author = "Eldwaib, Khalid and Grbović, Aleksandar and Kastratović, Gordana and Radu, Dorin and Sedmak, Simon",
year = "2017",
abstract = "In this study a central crack tension (CCT) specimen is chosen for analysis to demonstrate the capability and reliability of the extended finite element method (XFEM) in predicting the crack propagation trajectory and evaluating stress intensity factors (SIFs). This specimen is frequently used in fatigue tests for studying various effects on fatigue crack propagation and for obtaining crack growth properties of a material. The XFEM obtained SIFs solutions are compared with several well-known solutions from literature. Evaluation of fatigue life of the CCT specimen is also carried out and compared with the obtained by NASGRO.",
publisher = "Institut za ispitivanje materijala, Beograd",
journal = "Structural Integrity and Life",
title = "Fatigue life estimation of cct specimen using xfem",
pages = "156-151",
number = "2",
volume = "17",
url = "https://hdl.handle.net/21.15107/rcub_machinery_2728"
}

Eldwaib, K., Grbović, A., Kastratović, G., Radu, D.,& Sedmak, S.. (2017). Fatigue life estimation of cct specimen using xfem. in Structural Integrity and Life
Institut za ispitivanje materijala, Beograd., 17(2), 151-156.
https://hdl.handle.net/21.15107/rcub_machinery_2728

Eldwaib K, Grbović A, Kastratović G, Radu D, Sedmak S. Fatigue life estimation of cct specimen using xfem. in Structural Integrity and Life. 2017;17(2):151-156.
https://hdl.handle.net/21.15107/rcub_machinery_2728 .

Eldwaib, Khalid, Grbović, Aleksandar, Kastratović, Gordana, Radu, Dorin, Sedmak, Simon, "Fatigue life estimation of cct specimen using xfem" in Structural Integrity and Life, 17, no. 2 (2017):151-156,
https://hdl.handle.net/21.15107/rcub_machinery_2728 .