水平风洞中开展飞机尾旋特性研究的理论分析

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.