非旋转钝锥高超声速双平面拍摄风洞自由飞试验  

HYPERSONIC WIND TUNNEL FREE-FLIGHT TEST WITH BIPLANAR OPTICAL SYSTEM ON THE NON-SPINNING BLUNT CONE

作　　者：蒋增辉[1] 宋威[1] 陈农[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《力学学报》2015年第3期406-413,共8页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金资助项目(11202200)~~

摘　　要：在高超声速下(6马赫)开展了双平面拍摄风洞自由飞试验,对非旋转钝锥在小攻角下的运动特性和圆锥摆动问题进行了研究.试验结果表明,虽然只预置了攻角而无侧滑角,模型仍然全部出现了圆锥摆动,且在观察窗范围内侧滑角幅值均大于攻角幅值.模型角运动虽均处于小于10°的小攻角和小侧滑角状态,但阻尼力矩项呈现较为明显的非线性,而静力矩项的非线性较弱,近似为线性.5组实验中,有1组模型的角运动可能趋于极限平面运动或者是攻角幅值较小的极限圆锥运动,另外4组试验模型角运动显示出了趋于极限圆锥运动的趋势.尾端盖对模型的角运动影响不明显,而尾部对称布置的片条状凸起物对整个角运动幅值变化的稳定性存在明显影响,有凸起物的两组模型角运动幅值波动明显较小.To investigate the dynamic stability of the non-spinning blunt cone,wind-tunnel free-flight tests with biplanar optical system,were conducted at Mach 6 in the hypersonic wind tunnel.The tests show that coning motion appears for all the models,and in the range of viewing area the amplitude of angle of sideslip is larger than that of angle of attack,though,only angle of attack is preset.For all the models,the amplitude of both angles of attack and sideslip is no more than 10 degree,while damping moment shows obvious nonlinearity and static moment exhibits approximate linearity.One of the models shows the tendency of limit planar motion or limit coning motion with small amplitude of angle of attack,others all tend to limit coning motion.End cover has little effect on the angular motion of the models,while the protuberance symmetrically placed on the model tail can affect the transformation of amplitude of angular motion,and the fluctuation of angular motion amplitude is obviously smaller for models with strake.

关 键 词：风洞自由飞试验 双平面拍摄 极限圆锥运动 极限平面运动 高超声速 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]