无人机机翼主翼梁三维有限元分析及试验研究

The three-dimensional finite element analysis and the experimental study about the main spar of UAV wings

建立了某无人机主翼梁的三维有限元模型,应用多点约束模拟主翼梁外梁和中梁的连接,基于ANSYS软件,计算得到主翼梁应力分布和变形量,并与试验结果进行对比,吻合较好;分析结果表明:主翼梁强度满足设计要求,最大应力位于外梁和中梁的对接区周围,并且在此区域存在一个高应力梯度区域,该分析结果为机翼及主翼梁的优化设计提供了理论依据;这种有限元分析与试验验证相结合的思路,可为无人机(UAV)其他结构分析提供借鉴。

Three-dimensional finite element model of some UAV main spar has been established based on ANSYS. And MPC has been used to simulate the attachment between outside beam and inside beam. Compared the calculated stress and deformation with test results ,it has a good fit. The result indicated that the main spar intensity satisfies the design requirements, the maximum stress located at joint area between outside beam and inside beam, and has a high stress gradient region in this region;this analysis result has provided the theory basis for the wing and the main spar optimization design. The method of finite element analysis and experimental test may provide a reference for other UAV structure analysis.