10°尖锥标模高超声速动导数的实验测量  

10°Cone Model Free Flight Experiment in Hypersonic Impulse Type Wind Tunnel for Dynamic Stability Measurement

作　　者：马家驩[1] 潘文欣[1] 翟曼玲[1] 陈素贞[1] 

机构地区：[1]中国科学院力学研究所,北京100080

出　　处：《空气动力学学报》1997年第4期452-457,共6页Acta Aerodynamica Sinica

摘　　要：在中科院力学所JP－4B高超声速脉冲风洞中，用模型自由飞方法对1°尖锥开展动态实验测量，并用参数微分法辨识得到了该模型的俯仰阻尼导数。文中还介绍了在模型优化设计，模型工艺以及实验测量记录和数据判读技术方面的一些进展。实验结果表明；脉冲风洞中模型自由飞方法得到的10°尖锥标模高超声速动态气动特性测量值与国外可比数据一致，重复测量精度与弹道把试验相当。The paper describes the free flight experiment of 10°cone,as a calibration model, in hypersonic impulse type wind tunnel for dynamic stability study. Besides, the experimental technologies are also briefly developed. The experiments were carried out at Mach number of 9.9 in JF-4B Hypersonic Gun Tunnel, Institute of Mechanics, CAS. The pitch ing damp coefficients were derived by parameter differential method from the recorded angular motion of the model more than six cycles. The results show good agreement with the other's at same experimental conditions. The deviation of the four repeated shots is also in a reasonable range.

关 键 词：脉冲风洞 模型自由飞 动导数测量 高超声速 

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] V212.1