關鍵字查詢 | 類別:期刊論文 | | 關鍵字:Optimal Sizing and Cruise Speed Determination for a Solar-Powered Airplane

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1 98/2 航太系 馬德明 教授 期刊論文 發佈 Optimal Sizing and Cruise Speed Determination for a Solar-Powered Airplane , [98-2] :Optimal Sizing and Cruise Speed Determination for a Solar-Powered Airplane期刊論文Optimal Sizing and Cruise Speed Determination for a Solar-Powered AirplaneShiau, Jaw-Kuen; Ma, Der-Ming; Chiu, Chih-Wei; Shie, Jie-Ren淡江大學航空太空工程學系Reston: American Institute of Aeronautics and Astronautics, Inc.Journal of Aircraft 47(2), pp.622-629This paper presents the use of a genetic algorithm to optimize the size and cruise speed of a solar-powered manned aerial vehicle named Xihe. A conceptual aerodynamiccon figuration design is conducted first to obtainthe initial size of the aircraft and the performance parameters. The optimization process then searches for optimal solutions for minimum energy operation. To minimize the number of decision variables, the aspect ratio of the wing and the fuselage design are fixed during optimization. The mass of the Xihe aircraft is then parameterized as a function of two performance parameters: wingreference areaandcruise speed. Withthe parameterization results, a fittn
2 98/2 航太系 蕭照焜 教授 期刊論文 發佈 Optimal Sizing and Cruise Speed Determination for a Solar-Powered Airplane , [98-2] :Optimal Sizing and Cruise Speed Determination for a Solar-Powered Airplane期刊論文Optimal Sizing and Cruise Speed Determination for a Solar-Powered AirplaneShiau, Jaw-Kuen; Ma, Der-Ming; Chiu, Chih-Wei; Shie, Jie-Ren淡江大學航空太空工程學系Reston: American Institute of Aeronautics and Astronautics, Inc.Journal of Aircraft 47(2), pp.622-629This paper presents the use of a genetic algorithm to optimize the size and cruise speed of a solar-powered manned aerial vehicle named Xihe. A conceptual aerodynamiccon figuration design is conducted first to obtainthe initial size of the aircraft and the performance parameters. The optimization process then searches for optimal solutions for minimum energy operation. To minimize the number of decision variables, the aspect ratio of the wing and the fuselage design are fixed during optimization. The mass of the Xihe aircraft is then parameterized as a function of two performance parameters: wingreference areaandcruise speed. Withthe parameterization results, a fittn
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