Optimization of airplane wing structures under taxiing loads |
| |
| Affiliation: | 1. Cracow University of Technology, Jana Paw?a II 37 Street, Cracow, Poland;2. ABB Corporate Research, Starowislna 13A Street, Cracow, Poland;3. Warsaw University of Technology, Woloska 141 Street, Warsaw, Poland;1. UNIDEMI, Campus da Faculdade de Ciências e Tecnologia, Edifício VIII, 2829-516 Caparica, Portugal;2. Departamento de Engenharia Mecânica e Industrial, Faculdade de Ciências e Tecnologia - FCT, Universidade Nova de Lisboa, 2829-516 Caparica, Portugal;3. Laboratório Nacional de Engenharia Civil - LNEC, Departamento de Hidráulica e Ambiente, Av. do Brasil, 101, 1700-066 Lisboa, Portugal;1. Sagar Institute of Science & Technology (SISTec), Bhopal, Madhya Pradesh 462036, India;2. Department of Mechanical Engineering SISTec, Bhopal Madhya Pradesh 462036, India;3. Department of Mechanical Engineering, M.A.N.I.T., Bhopal, Madhya Pradesh 462003, India;1. Mechanical Engineering Department, Finolex Academy of Management and Technology, Ratnagiri, Maharashtra, India;2. Mechanical Engineering Department, Dr. Babasaheb Ambedkar Technological University, Raigad, Maharashtra, India;1. Toyota Motor Corporation, 1200 Mishuku, Susono-shi, Shizuoka-ken 410-1193, Japan;2. Quint Corporation, 1-14-1 Fuchu-cho, Fuchu, Tokyo 183-0055, Japan;1. Department of Mechanical Engineering, SSN College of Engineering, Chennai-603110, India;2. Department of Mechanical Engineering, Dhanalakshmi Srinivasan College of Engineering and Technology, Mamallapuram-603104, India;3. Department of Industrial Engineering, Anna University, Chennai-600025, India |
| |
| Abstract: | A methodology is presented for the optimum design of aircraft wing structures subjected to taxiing loads. The dynamic stresses induced in the wing as the airplane accelerates or decelerates on the runway during take-off or landing are computed by considering the interaction between the landing gear and the flexible airplane structure. The procedure is capable of taking into account both the effects of discrete runway bumps and the effects of runway unevenness. A numerical step-by-step method is developed for solving the nonlinear differential equations of motion. The optimization methodology is illustrated with two examples. The first example deals with the design of the typical section (symmetric double wedge airfoil). This example is studied by using a graphical procedure mainly to understand qualitatively the behavior of wing structures under taxiing loads and also to obtain a physical insight into the nature of the optimum solution. The second example is concerned with the design of a more realistic wing structure. In this case, the problem is formulated and solved as a constrained nonlinear programming problem based on finite element modeling. |
| |
| Keywords: | |
| 本文献已被 ScienceDirect 等数据库收录！ |
|
