Modelling of geometrically nonlinear structure of large flexible wing based on CR theory
Received date: 2017-05-25
Revised date: 2017-07-04
Online published: 2017-07-04
Supported by
Provincial/Ministerial Level Project
王伟 , 段卓毅 , 耿建中 , 张健 , 李军府 . 基于CR理论的大柔性机翼几何非线性结构建模[J]. 航空学报, 2017 , 38(S1) : 721544 -721544 . DOI: 10.7527/S1000-6893.2017.721544
The large flexible wing under aerodynamic loading is subject to distinct large deformation. Therefore, the assumption of small deformation according to the classical linear theory no longer holds, and structural modeling of such wing should consider the geometrically nonlinear effect. Based on Co-Rotational (CR) theory, the geometrically nonlinear large deformation is resolved into rotation and translation of the rigid body and elastic deformation described in the local coordination system. The structural model for description of the geometrically nonlinear deformation of the large flexible wing is constructed in this paper. With the large flexible camber beam as an example, the geometric nonlinear large deformation under the moment load is studied using the increment iterated method. The static method is validated, and the effect of geometrical nonlinear deformation due to coupling load is discussed. The geometrical nonlinear large deformation of a solar Unmanned Aerial Vehicle (UAV) with the layout similar to "Helios" is also studied.
Key words： large flexible; geometrically nonlinear; CR theory; statics; large deformation
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