Static Structural Analysis of a Variable Span Morphing Wing for Unmanned Aerial Vehicle 机翻标题: 暂无翻译,请尝试点击翻译按钮。

会议集名/来源
International Conference on Aerospace and Mechanical Engineering: AeroMech17 : Recent Advancements and Innovations in Aerospace & Mechanical Engineering, Batu Ferringhi, Malaysia, 21-22 November 2017
出版年
2018
页码
321-329
会议地点
Batu Ferringhi
作者单位
School of Aerospace Engineering,Universiti Sains Malaysia,Engineering Campus,Nibong Tebal,Pulau Pinang,Malaysia
作者
M Bashir;P Rajendran
摘要
While the primary reason to develop an adaptive wing is the aerodynamic benefits,the primary hindrance is the structural and vibrational considerations due to the unsteady nature of the airflow during the flight.Hence this study forms an important part of the morphable wing technology.In this paper,the design of a moderate aspect ratio variable span wing will be performed;The morphing wing is modeled structurally to observe the effect of spanwise load distribution on the wing structure.For the structural design and analysis of the unmanned aerial vehicle(UAV)under this study,commercial software Solidworks and Ansys/Static Structural/Modal are used.The static structural analyses of the wing are performed under different load conditions.The results of these analyses show that the designed structure is safe within the flight envelope.It is observed that the wing-root bending moment increases drastically due to an increase in the wingspan.Thus,the bending moment along the wingspan of the morphing wing is much larger than that of the conventional wing which results in an increase in the deflection of the free-end.The maximum stress for the un-extended wing configuration increases for the extended wing configuration.
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