大攻角非定常气动力建模及飞机纵横向气动力仿真

发布时间：2018-02-07 16:22

本文关键词： 风洞实验大振幅耦合运动非定常空气动力外插迟滞特性　出处：《南京航空航天大学》2015年硕士论文　论文类型：学位论文

【摘要】：本文在NH-2低速风洞中对某背景机标模进行了大振幅运动动态实验,实验测量了该模型单自由度俯仰运动、俯仰滚转耦合运动、不同支撑攻角下的单自由度滚转运动以及50°支撑攻角下横向耦合运动时的非定常气动力,分析了上述各种运动下该模型的非定常气动特性。采用模型动态运动风洞试验结果作为样本数据,提出了基于攻角变化的??纵向气动模型和基于侧滑角变化的?横向气动模型,分析了该模型的“外插”特性,提出了一种线性“外插”的方法,并通过经典的风洞试验数据进行了验证。在此基础上完善了建模方法,完成了背景机标模的纵向运动和横向运动非定常气动力数学模型。采用上述非定常气动力数学模型,基于单自由度滚转运动的样本数据,计算了俯仰滚转耦合运动时的横向非定常气动力;基于单自由度俯仰运动的样本数据,计算了俯仰滚转耦合运动的纵向非定常气动力;基于偏航滚转耦合运动的样本数据,计算了旋转流场下单自由度偏航运动和滚转运动的非定常气动力。计算结果表明与试验结果吻合较好,验证了数学模型的准确性。
[Abstract]:In this paper, the large amplitude motion dynamic experiment of a background machine model is carried out in NH-2 low speed wind tunnel. The single degree of freedom pitch motion and pitch roll coupling motion of the model are measured experimentally. The unsteady aerodynamic force of the single degree of freedom rolling motion at different angles of attack and the transverse coupled motion at 50 掳supporting angle of attack, The unsteady aerodynamic characteristics of the model under the above motions are analyzed. The dynamic motion wind tunnel test results of the model are used as the sample data, and the change of attack angle is proposed. ? Longitudinal aerodynamic model and based on lateral slip angle variation? In this paper, the "extrapolation" characteristic of the model is analyzed, and a linear "extrapolation" method is proposed, which is verified by classical wind tunnel test data. In this paper, the unsteady aerodynamic mathematical models of longitudinal and transverse motion of the background machine model are completed. The above unsteady aerodynamic mathematical model is adopted, and the sample data of the rolling motion of single degree of freedom are used. The transverse unsteady aerodynamic force of the pitching roll coupled motion is calculated, the longitudinal unsteady aerodynamic force of the pitch roll coupled motion is calculated based on the sample data of the single degree of freedom pitch motion, and the sample data of the yaw roll coupled motion are calculated. The unsteady aerodynamic forces of yaw motion and rolling motion of degree of freedom issued by rotating flow field are calculated. The results show that the results are in good agreement with the experimental results and the accuracy of the mathematical model is verified.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V211.74

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