FL-13风洞突风发生装置研究

为在 FL-13风洞中开展飞机全模突风响应试验研究，建立研究所需的突风发生装置，进行了突风发生装置的研究。研究中，从大飞机突风试验需求出发，确定了装置的技术指标，通过数值模拟计算，固化了装置技术指标；通过引导性试验和总体方案对比，选定了单电机驱动双飞轮及曲柄连杆方案；通过动力学分析、结构设计与有限元分析、模态分析和疲劳分析，解决了装置共振、刚度增加困难和安装空间受限等问题；通过装置调试与突风流场考核结果表明，研制的 FL-13风洞突风响应试验装置实现了在来流40 m／s 的风速范围内按正弦规律变化产生突风，模型中心处最大突风振幅达到9 m／s。突风流场的成功模拟，标志着 FL-13风洞具备了开展大展弦比飞机突风响应影响试验研究的能力。

Investigation on gust response test apparatus in FL-13 wind tunnel

Gust response test apparatus are investigate to satisfy the need of gust response test for a full aircraft model in CARDC FL-13 wind tunnel.The apparatus requirements for a large transporter gust response test is confirmed based on CFD simulations.Mechanism design is determined through some introductory tests and the comparison of overall scheme.The detailing problems,such as resonance vibration,difficulty of stiffness enhancement,limitation of installa-tion space and so on,are solved by means of dynamic analysis,structure design and finite ele-ment analysis,mode analysis and fatigue analysis.The Debugging test and the examining of gust flow field qualities show that:gust response test apparatus developed hence can generate sinu-soidal gust wind with the speed of 40m/s in FL-13 wind tunnel.The maximum speed amplitude of gust in the center of model can reach up to 9m/s.The successful simulation of gust flow field indicates the ability of gust response test for high-aspect-ratio aircraft in FL-13 wind tunnel.