轻质量低成本无人机舵面结构优化与验证

复合材料蜂窝夹芯结构因其高比强度、比模量及可设计性而广泛应用于航空飞行器结构。文章提出了 1种轻质量、低成本舵面结构方案——通过增大蜂窝芯密度使其剪切模量提高,进而降低复合材料面板应力水平,减小面板厚度。首先,根据理论选择通过增大蜂窝密度提升蜂窝剪切模量；然后,对结构进行有限元计算与分析,发现蒙皮应力水平随蜂窝芯剪切模量增大而显著降低；最后,设计不同蜂窝芯密度的蜂窝夹芯结构进行试验。试验结果证明,蜂窝芯越致密,其典型力学性能越高,冲击后的剩余强度也越高。

Optimization and Verification of Lightweight Low-Cost UAV Rudder Structure

Composite honeycomb sandwich structures are widely used in aircraft structures due to their high specific strength, specific modulus and designability. A lightweight and low-cost rudder structure scheme is proposed to increase the shear modulus by increase the density of the honeycomb core, thereby reducing the stress level of the composite panel and reducing the thickness of the panel. The rudder structure is designed and the optimization scheme is verified through finite element simulation calculation and experiment. Firstly, according to the shear modulus theory of honeycomb core, the honeycomb density that improves the shear modulus of honeycomb is selected. Secondly, finite element calculation and analysis are carried out on the structure, and it is found that the stress level of the skin decreases significantly with the increase of the shear modulus of the honeycomb core. Finally, honeycomb sandwich structures with different honeycomb core densities are designed for testing. The test results show that the denser the honeycomb core is, the higher its typical mechanical properties are, and the higher its residual strength after impact is. Both numerical simulation and experimental results verify the feasibility of this lightweight and low-cost UAV rudder structure optimization scheme.