高速风洞动导数试验精准度提升研究  

Investigation on the high-speed wind tunnel dynamic derivative test accuracy promotion

作　　者：潘金柱[1] 张杰[1] 才义 徐明[1] 

机构地区：[1]中航工业空气动力研究院高速高雷诺数重点实验室,辽宁沈阳110034

出　　处：《空气动力学学报》2016年第5期606-610,共5页Acta Aerodynamica Sinica

摘　　要：随着高机动性飞行器的发展,准确获取飞行器的动导数尤为重要,进而对传统动导数试验技术的精准度要求越来越高。然而,在高速风洞试验中,由于模型尺寸小、气动载荷大、振动幅值小,与低速动导数试验相比,高速动导数试验面临的困难更大。为了提高高速动导数的试验精准度,针对以上特点,对模型在振动过程中的受力情况、振动机构设计以及信号干扰等问题进行了详细分析与总结,并应用于型号试验中,试验结果显示高速风洞动导数重复性精度提高至10%以内。通过所做的研究工作,高速动导数试验技术得到了提升,同时,文中对高速动导数试验技术的未来发展趋势也做了简要介绍。Accurate dynamic derivative is particularly important with the development of modern high-maneuverability flying vehicles.The requirement of dynamic derivative wind-tunnel test technique is much stricter in precision and accuracy nowadays.High-speed dynamic derivative tests face more difficulties compared to low-speed ones due to small size of the model and high aerodynamic loads, small oscillation amplitude. According to the characteristics mentioned above,stress situation study during model oscillation,oscillation mechanism design and signal interference are analyzed and summarized in details,which are all applied on production test model in the wind tunnel.The results showed that the high-speed wind tunnel dynamic derivative repeatability increase to less than 10%.Through the research work done,the high-speed dynamic stability derivatives measurement technique has been improved.Also the developing trendy of the high-speed dynamic stability derivatives measurement test technique is briefly presented.

关 键 词：高速风洞 动导数 振动机构 信号干扰 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]