基于多项式修正片条气动力的跨音速颤振分析方法及其试验验证  

Transonic flutter analysis method based on polynomial modified strip aerodynamic force and its test verification

作　　者：张婷婷 周健斌[1] 窦忠谦[1] 章俊杰[1] ZHANG Tingting;ZHOU Jianbin;DOU Zhongqian;ZHANG Junjie(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《振动与冲击》2022年第1期19-23,共5页Journal of Vibration and Shock

摘　　要：提出一种基于多项式修正片条气动力的跨音速颤振分析方法,以片条内升力和力矩随攻角变化斜率为修正目标,采用多项式方程模拟片条力矩分布,使整个翼面的气动力大小和分布都与目标相符,进而使用修正后的气动力进行跨音速区的颤振分析。计算结果经跨音速颤振风洞试验验证,该方法对翼吊发动机构型的机翼颤振型、带操纵面的尾翼颤振型都有较高的计算精度,计算获得的跨音速压缩性“凹坑”特性与试验结果吻合较好。Here,a transonic flutter analysis method based on polynomial modified strip aerodynamic force was proposed.Taking the slope of lift and moment in the strip with variation of attack angle as the modification target,the strip moment distribution was simulated with polynomial equations to make aerodynamic force and its distribution on the whole wing surface be consistent with the target,and then the modified aerodynamic force was used for transonic flutter analysis.The calculation results were verified with transonic flutter wind tunnel tests.It was shown that the proposed method has higher calculation accuracy for wing flutter mode of wing crane engine configuration and tail flutter mode with control surface;the transonic compressibility“pit”characteristics obtained by calculation agree better with test results.

关 键 词：跨音速颤振 偶极子格网法(DLM) 气动力修正 风洞试验 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]