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Marshal Deep Kafle,Nikesh Bhattarai,Hyeon Beom Jo,Kyoung Mu Min,Han Yeong Baek,Byoung Soo Kim,Sung Hun Kim 한국항공우주학회 2015 한국항공우주학회 학술발표회 논문집 Vol.2015 No.4
Joined-wing UAV, known for its light weight, high stiffness and resistance to bending, better aerodynamic efficiency has been an air vehicle of interest for many researchers. In this paper, two types of configuration of Joined-Wing UAV are designed and the one better suiting the mission objective is further analyzed numerically. Its flight performance is further analyzed for varying weight and wingspan and the design fulfilling the mission requirements is examined. CFD analysis for the full scale model is also performed, followed by static structural analysis of composite structures. Its static and dynamic stability are also numerically studied. The analyses show satisfying results, based on which a halfscaled model is manufactured and flight test is performed to study and determine the control-law structure of the aircraft and to set the control-law design parameter for static performance. The results presented are a basis for the manufacture of full scale UAV.