大展弦比无人机高速风洞测力试验技术研究

Research on force test technique of UAV model with large aspect ratio in high speed wind tunnel

本文针对大展弦比无人机布局特点,开展了2.4m风洞测力试验技术研究,主要包括专用高精度大载荷天平研制、支撑系统的优化设计、支撑干扰的有效扣除等,利用CFD手段和ANSYS分析软件,有效地建立了大展弦比无人机高速风洞测力试验技术,并成功投入应用,获得了满意的试验结果。

In accordance with the configuration characteristics of UAV model with large aspect ratio, force test technique in 2.4m wind tunnel was developed, including the design of special high-precision and largeload balance, the design of strut system, the deducting of the interference of strut and so on. With the help of CFD and software of ANASYS, force test technique of UAV model with large aspect ratio was established in high speed wind tunnel, which had been used in tests and had acquired satisfying results.