摘要
风洞模型自由翻滚动导数试验技术是为满足航空航天飞行器 0°～ 36 0°全迎角范围内的动导数测量及产生极限环振动现象研究之急需而研制的。该项试验技术研制了 0 .6m跨超声速风洞和 0 .5m高超声速风洞采用液体轴承支撑的自由翻滚试验装置 ;研制了高精度的角度测试系统与系统建模的大迎角非线性数据处理技术。
The wind tunnel test technique for model free to tumble dynamic derivatives has been developed to meet the urgent needs for dynamic derivative measurements of aerospace aircraft models in the range of angles of attack of 0°～360°and to meet the needs for mechanism study of limit cycle oscillation phenomena. The related test devices based on liquid bearing for the 0.6m transonic and 0.5m diahypersonic wind tunnels, the angularity measurement system with high accuracy and the non linear system identification data processing technique have been developed. This technique has been successfully applied in providing the applicable test results for escape capsule model.
出处
《空气动力学学报》
CSCD
北大核心
2000年第4期383-389,共7页
Acta Aerodynamica Sinica
关键词
动导数
自由翻滚
试验技术
风洞模型
逃逸飞行器
dynamic stability derivative
free to tumble
test technique
liquid bearing
system identificat$
