某无人机复合材料机翼结构强度的有限元分析
Finite Element Analysis of Structural Strength of a UAV Composite Wing
王尕平 1姚作霖 2郑会龙 3宣凯涛3
作者信息
- 1. 大连交通大学 土木工程学院,大连 116028
- 2. 大连交通大学 土木工程学院,大连 116028;滨州魏桥国科高等技术研究院,滨州 256600
- 3. 中国科学院 工程热物理研究所,北京 100190;轻型涡轮动力全国重点实验室,北京 100190
- 折叠
摘要
针对某型亚音速无人机的承力要求,为评估机翼的刚度和强度,在CFD软件中对无人机进行了三种工况下的气动性能分析,并将CFD软件计算所得的压强作为外载荷施加在机翼表面,在有限元软件中对机翼进行强度校核.研究结果表明,翼面压力、机翼的变形和应力、机翼填充泡沫的应力均随着侧滑角的增加而增大,翼梁的应力则反之.机翼的变形量不大于半翼展长度值的5%;机翼蒙皮、翼梁和机翼填充泡沫的最大应力分别为62.68、14.3和0.95MPa,均小于材料的许用应力,机翼各结构的强度和机翼的整体刚度满足设计要求.
Abstract
Aiming at the force-bearing requirements of a certain type of subsonic UAV,in order to evaluate the stiffness and strength of the wing,the aerodynamic performance of the UAV was analyzed under three working conditions using CFD software,and the pressure obtained from the CFD software calculation was applied to the wing surface as an external load,then the strength of the wing was calibrated in the finite element software.The results show that the pressure on the wing surface,the deformation and stress of the wing,as well as the stress of the wing filling foam increase with the increasing side-slip angle,conversely,the stress of the wing beam decreases.The deformation of the wing is not more than 5%of the half wingspan length,the maximum stresses of the wing skin,wing beam,and wing filling foam are 62.68MPa,14.3MPa,and 0.95MPa,respectively,which are less than the allowable stresses of the materials,the strengths of each structure of the wing and the overall stiffness of the wing meet the design requirements.
关键词
机翼/复合材料/有限元分析/结构强度/无人机Key words
wing/composite material/finite element analysis/structural strength/unmanned aerial vehicle引用本文复制引用
出版年
2024
NETL
NSTL
万方数据