Realization of an optimized wing camber by using formvariable flap structures |
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| Institution: | 1. School of Aerospace, Mechanical and Manufacturing Engineering, RMIT University, Melbourne 3083, Australia;2. senseFly SA, Route de Genève 38, 1033 Cheseaux-Lausanne, Switzerland;3. Advanced Composites Centre for Innovation and Science, University of Bristol, Bristol BS15TU, UK;1. University of Southampton, Southampton, SO17 1BJ, UK;2. Swansea University, Singleton Park, Swansea, SA2 8PP, UK;1. School of Mechanical and Electrical Engineering, China Jiliang University, Hangzhou, China;2. Key Laboratory of Intelligent Manufacturing Quality Big Data Tracing and Analysis of Zhejiang Province, China Jiliang University, China;3. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou, China;4. Key Laboratory of Soft Machines and Smart Devices of Zhejiang Province, Zhejiang University, China;5. School of Astronautics, Northwestern Polytechnical University, Xi''an, China;6. School of Mechanical Engineering, Hangzhou Dianzi University, Hangzhou, China;1. Chinese Aeronautical Establishment, Beijing 100012, China;2. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;3. Aircraft Strength Research Institute of China, Xi’an 710065, China;4. Graduate School of Chinese Aeronautical Establishment, Yangzhou 225002, China |
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| Abstract: | According to market research predictions, a large growth in the number of passengers as well as airfreight volume can be expected for the civil transport aircraft industry. This will lead to an increased competition between aircraft manufacturers. To stay competitive it will be essential to improve the efficiency of new generation of aircraft. Transonic wings of civil aircraft with their fixed geometry offer an especially large potential for improvement. Such fixed geometry wings are optimized for only one design point, characterized by the following parameters: altitude, mach number and aircraft weight. Since these vary permanently during the mission of the aircraft the wing geometry is rarely optimal. As aerodynamic investigations have shown, one possibility to compensate for this major disadvantage lies in the chordwise and spanwise differential variation of the wing camber for mission duration. This paper describes the design of a flexible flap system for an adaptive wing to be used in civil transport aircraft that allows both a chordwise as well as a spanwise differential camber variation during flight. Since both lower and upper skins are flexed by active ribs, the camber variation is achieved with a smooth contour and without any additional gaps. This approach for varying the wing's camber is designed to be used for replacement and enhancement of a given flap system. In addition, the kinematics of the rib structure allows for adaptation of the profile contour to different types of aerodynamic and geometric requirements. |
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