俯仰角对鸭式布局飞机摇滚运动的影响与机理分析

摘要

为了研究鸭式布局飞机的摇滚运动,设计了一种包括鸭翼、脊型前体、边条翼、主翼和垂尾的模型,进行滚转自由度释放、静态测力、动导数试验和烟线流场显示多种技术手段相结合的风洞试验.首先为了得到摇滚从发生到消失的全过程,进行了俯仰角范围为12° ~52°、间隔1°测量的滚转自由度释放试验;结果表明对应于不同的俯仰角,鸭翼布局飞机的摇滚运动也具有不同的性质,其平衡点和运动形式均发生变化.接着静态测力和动导数试验证实;在翼体结构的多涡系影响下,摇滚可在零度平衡点和非零平衡点位置处发生;且运动可为极限环和非极限环形式.最后通过流场显示,分析了在不同迎角时鸭式布局飞机形成翼体摇滚的可能的流动机理.%To study wing-body rock of canard-configuration aircrafts, a model for wind tunnel test was designed having a chine forebody, canard wings, strake wings,main wings, and a vertical fin.This model was tested by different methods including free rolling motion, static force balance test, dynamic derivative test, and smoke wire technique.First, the complete rock process was studied by free-to-roll experiment in the range of pitch angel θ=12°~52° and Δ=1°.The results show that, rolling motions of the canard-configuration aircraft have several different mean roll angles and motion forms vary with different pitch angles.Second, the results of the static force balance test and dynamic derivative test confirm that the rolling motion can occur around zero or nonzero equilibrium roll angles with limit-cycle forms or nolimit cycle ones due to the influence of multi-vortex structures.Finally, the flow visualization tests show that the main vortices generate the wing-body rock at different stages.The possible mechanism for the wing-body rock was also analyzed for the canard-configuration aircraft.