摘要
为提升高超声速气动试验模拟能力,建设了大型高超声速风洞。高超声速风洞的试验段为喷管、模型姿态控制机构、光学测量仪器提供结构平台,针对其隔震性能差、安全性差、安装繁琐的缺点进行优化设计。新试验段采用充气密封装置、安全门、液压顶盖,提高了风洞生产率和工作人员的安全保障,降低了劳动强度。
To improve the ability of hypersonic aerodynamics test,a new hypersonic wind tunnel was built.The test section of hypersonic wind tunnel provides structural platform for nozzles,control mechanism of model attitude and optical measuring instrument.In view of the shortcomings of poor shock isolation,poor safety,and complicated installation in the traditional test section of hypersonic wind tunnel,the new test section uses inflatable sealing device,safety gates,hydraulic top covers,which improves wind tunnel productivity and personnel safety,and reduces labor intensity.
引文
[1]唐志共,许晓斌,杨彦广,等.高超声速气动力试验技术进展[J].航空学报,2015,36(1):96-97.
[2]胡世祥.高超声速试验设备设计[M].北京:国防工业出版社,2001.
[3]孙启志.一种负压环境下充气密封装置:中国,881056078[P].2015-08-12.