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  • 1.
    Melin, Tomas
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Rizzi, Arthur
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Stamblevski, Christopher
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Isikveren, Askin
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Anders, Hanyo V.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    How Industry Concepts of Concurrent Engineering Enhances Aircraft Design Education2007In: Proceedings of the Institution of Mechanical Engineers. Part G, Journal of Aerospace Engineering, ISSN 0954-4100, E-ISSN 2041-3025, Vol. 221, no 2, p. 175-192Article in journal (Refereed)
    Abstract [en]

    Two student projects are described including the intended goals, the approaches taken, the tools used, and what was learned from the exercises. An international collaborative teaching protocol between Ecole Polytechnique de Montreal and the Royal Institute of Technology (KTH) was exercised in aircraft design education. Poignantly, a novel instructive design process using the analogue of contemporary concurrent engineering practices in industry was implemented. The idea was to strategically assign multi-disciplinary design tasks to each Partner University in accordance with their respective competencies. The university-industry coupling was initiated by request for proposals and corresponding marketing requirements and objectives produced by Bombardier Aerospace in Montreal, Canada. Two MATLAB™-based tools were prominent in facilitating the capstone aircraft design projects. They included: Quick Conceptual Aircraft Research and Design, a computer-aided conceptual design engineering system; and TORNADO, a Vortex-Lattice code for computing aerodynamic characteristics. The result of the two exercises was found to benefit the participating industry, the educational establishments involved, and the students carrying out the projects.

  • 2.
    Stamblewski, Christopher
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Sankar, B. V.
    Zenkert, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Three-dimensional quadratic failure criteria for thick composites using the Direct Micromechanics Method2007In: American Society for Composites - 22nd Technical Conference of the American Society for Composites 2007 - Composites: Enabling a New Era in Civil Aviation, 2007, p. 612-631Conference paper (Refereed)
    Abstract [en]

    Majority of failure criteria currently used for unidirectional fiber composites assume a state of plane stress and are therefore only applicable to thin laminates. As fiber composites are also used in thick structures with significant out of plane stresses, new failure criteria are required. The Direct Micromechanics Method, DMM, is used to determine the exact failure envelope of a unidirectional graphite/epoxy composite. A hexagonal unit cell of the composite is modeled using finite elements. Assuming that the failure criteria for the fiber and matrix materials and for the interface are known, the exact failure envelope is constructed from several three-dimensional stress states that correspond to failure initiation in the composite. These 3D failure stress states are then used to develop five three-dimensional phenomenological failure criteria: Maximum Stress, Maximum Strain, Quadratic Stress, Quadratic Strain and Optimized Quadratic Failure Criteria. These criteria are compared with the DMM failure envelope and with available 2D failure criteria. It is observed that the 3D Quadratic Stress and Strain Failure Criteria may be open, meaning that they predict infinite strength in some directions. However, they can be made closed in combination with the Maximum Stress or the Maximum Strain Failure Criterion. It is observed that a combination of aforementioned 3D failure criteria make failure prediction in thick composites more accurate and reliable and is comparable to that of Tsai-Wu criterion for thin composites under plane stress conditions. The proposed Optimized Quadratic Failure Criteria is always closed and is more reliable than all other 3D criteria.

  • 3.
    Stamblewski, Christopher
    et al.
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
    Sankar, Bhavani V
    Zenkert, Dan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Lightweight Structures.
    Analysis of three-dimensional quadratic failure criteria for thick composites using the direct micromechanics method2008In: Journal of composite materials, ISSN 0021-9983, E-ISSN 1530-793X, Vol. 42, no 7, p. 635-654Article in journal (Refereed)
    Abstract [en]

    Currently fiber composites are used in thick structures with significant out of plane stresses for which new 3D failure criteria are required. In this article the direct micromechanics method is used to deter-mine the exact failure envelope of a unidirectional graphite/epoxy composite. A hexagonal unit cell of the composite is modeled using finite elements. Assuming that the failure criteria for the fiber and matrix materials and for the fiber-matrix interface are known, the exact failure envelope is constructed from a large number of three-dimensional stress states that correspond to failure initiation in the composite. These 3D failure stress states are then used to develop five three-dimensional phenomenological failure criteria: maximum stress; maximum strain; quadratic stress; quadratic strain; and optimized quadratic failure criteria. It is observed that the 3D quadratic stress and strain failure criteria may not always be closed, that is, they predict infinite strength in some directions. They can be made closed in combination with the maximum stress or the maximum strain failure criterion. It is found that a combination of aforementioned 3D failure criteria make failure prediction in thick composites more accurate and reliable. It is noted that the newly proposed optimized quadratic failure criteria is always closed, and is found to be more reliable than all other 3D failure criteria.

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