基于大振幅谐波运动的非定常气动模型风洞实验验证  

The validation of unsteady aerodynamic model based on the high amplitude harmonic rolling motion test

作　　者：史志伟[1] 吴根兴[1] 黄达[1] 

机构地区：[1]南京航空航天大学空气动力学系,江苏南京210016

出　　处：《空气动力学学报》2010年第6期650-654,共5页Acta Aerodynamica Sinica

摘　　要：利用大振幅动态实验装置,完成了某飞机在给定支撑角下的单独滚转大振幅谐波振荡实验;基于所获得的实验数据,应用模糊逻辑建模方法建立了单独滚转运动的非定常气动力模型;应用等效缩减频率计算方法,计算了飞机模型按锯齿波运动时等效缩减频率的变化,并带入非定常气动力模型中进行仿真计算;最后与实验测量获得的锯齿波运动气动力数据进行了比较。研究结果表明,仿真计算结果与实验测量结果符合较好,反映出用大振幅谐波振荡实验数据建立的滚转运动非定常气动力模型能很好地反映模型的滚转运动非定常气动特性。Using the 2D dynamic experimental apparatus,the high amplitude harmonic rolling motion tests of an aircraft are conducted.Using the Fuzzy Logic Model method,the unsteady aerodynamic model based on oscillation test data is developed.The equivalent reduced frequency needed in the unsteady model is numerically calculated by using a limited prior time history of state variables in a least-square sense.The unsteady roll moment of the aircraft rolling with the sawtooth motion are calculated by using this unsteady model and compared with the test data.The results show that the simulation results are coincident basically with the test data.It is also concluded that the unsteady model based on the high amplitude harmonic rolling oscillation test data is effective to calculate the unsteady aerodynamic characteristics of rolling motions.

关 键 词：谐波运动 非定常气动模型 等效缩减频率 风洞实验 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]