水平风洞中开展飞机尾旋特性研究的理论分析

以某飞机尾旋特性为例，在水平风洞中利用具有3自由度的模型支撑装置开展飞机尾旋特性研究并进行理论分析；将基于3自由度装置的建模仿真结果与传统的6自由度飞行仿真、立式风洞尾旋试验结果进行对比，结果显示，三者具有较好的一致性；利用3自由度支撑装置开展飞机尾旋特性研究还可获得飞机尾旋进入和发展阶段的运动参数，可实现尾旋进入、发展及改出的全过程模拟。同时，研究了支撑装置曲杆惯量、机构摩擦和质心偏离等因素对飞机尾旋特性试验结果的影响，结果表明在曲杆及飞机模型设计时，需严格控制曲杆惯量和质心偏移，机构摩擦对试验结果的影响不大。

Theoretical analysis of research on aircraft spin characteristic in horizontal wind tunnel

Theoretical analysis of investigation of characteristics of an aircraft spin using an actively controlled scaled model of a 3-DOF gimbal in the horizontal wind tunnel is given. The simulation results based on the 3-DOF rig are compared with results of the conventional 6-DOF simulation and free flight spin test, and a good agreement between them is observed. Moreover, the motion parameters during the spin entry and developing phase can be obtained using the 3-DOF rig, which enables simulation of the whole process from spin entry to developing and to recovery. Meanwhile, the effects of dynamics of the rod, gimbal friction moments and shift of the center of gravity in the model relative to the center of the gimbals are considered. The results show that the inertia of the rod and shift of the center of gravity should be strictly controlled during the design phase, and that friction has small influence on spin behaviors.