Optimal design of composite lattice shell structures for aerospace applications |
| |
| Authors: | G Totaro Z Gürdal |
| |
| Institution: | 1. CIRA – Italian Aerospace Research Center, Via Maiorise snc, 81043, Capua (CE), Italy;2. Delft University of Technology, Kluyverweg 1, 2629 HS Delft, The Netherlands;1. Department of Aerospace Engineering, Siberian State Aerospace University, Krasnoyarsk, Russia;2. School of Engineering and Information Technology, University of New South Wales at the Australian Defence Force Academy, Canberra, Australia;1. High Speed 3D Printing Research Center, National Taiwan University of Science and Technology, No. 43, Section 4, Keelung Road, Taipei 106, Taiwan, ROC;2. Department of Mechanical Engineering, National Taiwan University of Science and Technology, No. 43, Section 4, Keelung Road, Taipei 106, Taiwan, ROC;3. Department of Industrial and Systems Engineering, The Hong Kong Polytechnic University, Hung Hom, Kowloon 999077, Hong Kong Special Administrative Region, China;4. Graduate Institute of Biomedical Engineering, National Taiwan University of Science and Technology, No. 43, Section 4, Keelung Road, Taipei 106, Taiwan, ROC;5. Consultant Professor, LungHwa University of Science and Technology, Taiwan, ROC;1. Department of Aerospace Engineering, Siberian State Aerospace University, Krasnoyarsk, Russia;2. School of Engineering and Information Technology, University of New South Wales at the Australian Defence Force Academy, Canberra, Australia;1. Department of Enterprise Engineering - University of Rome Tor Vergata, Via del Politecnico, 1, 00133, Rome, Italy;2. DEIM, University of Tuscia, Largo dell’Università, 01100 Viterbo, Italy |
| |
| Abstract: | An optimization method for composite lattice shell structures under axially compressive loads is proposed aiming at the preliminary design. The method implements and improves some previous results of the fully analytical approach which is currently adopted at the state-of-the-art. The fully analytical approach provides the minimum mass solution under buckling and strength constraints, irrespective of other possible design limitations, such as, shell stiffness constraints. As a consequence, the minimum mass solution turns out to be satisfactory whereas other requirements are absent or automatically achieved but, on the contrary, it can drive the final preliminary configuration far from the real optimum.The proposed method implements numerical minimization allowing the designer to easily handle suboptimal configurations which are located in the vicinity of the minimum mass solution. When stiffness requirement is present (as in most cases) the benefit of this approach – in terms of weight saving with respect to the analytical design – is finally shown with a practical example. |
| |
| Keywords: | |
| 本文献已被 ScienceDirect 等数据库收录！ |
|
