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.
出处
《空气动力学学报》
CSCD
北大核心
1997年第4期452-457,共6页
Acta Aerodynamica Sinica
关键词
脉冲风洞
模型自由飞
动导数测量
高超声速
impulse type wind tunnel
model free flight
dynamic stability derivatives
pitching damp coefficient
