常规高超声速风洞模型自由飞试验发射装置设计与应用  

Design and application of launch device for free-flight test in hypersonic wind tunnel

作　　者：何超[1] 谢飞[1] 许晓斌[1] 陈磊[1] HE Chao;XIE Fei;XU Xiaobing;CHEN Lei(Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,四川绵阳621000

出　　处：《实验流体力学》2021年第5期121-127,共7页Journal of Experiments in Fluid Mechanics

摘　　要：自由飞模型发射技术是自由飞试验技术的关键技术之一。针对常规高超声速风洞,中国空气动力研究与发展中心超高速空气动力研究所对模型发射装置进行了详细设计与分析,并采用典型外形模型在某高超声速风洞上开展了模型自由飞试验(试验马赫数6.0)。试验结果表明:装置发射效果良好,模型发射后姿态平稳;根据不同风洞具体情况进行适应性尺寸改造,发射装置能够广泛应用于常规高超声速风洞自由飞试验。在发射装置结构设计时,模型的发射压力与发射速度应作为重要参数加以考虑;模型夹持器需根据模型的不同外形进行适应性设计。The Free-flight test launch technology is one of the key technologies in the free-flight test.Hypervelocity Aerodynamics Institute,CARDC,researched and developed the model launch device for the conventional hypersonic wind tunnel,and conducted a series of free-flight tests in the hypersonic wind tunnel with Mach number being 6.The free-flight test results indicate that:the launch device worked well,and the attitude of the model is stable.According to the different wind tunnel specific circumstances,the size of the launch device can be reformed,which can be applied to different hypersonic wind tunnels.Launch pressure and launch velocity are important parameters,which should be considered at the structure design stages.The model fixed component also needs the adaptability design according to the different model shapes.

关 键 词：高超声速风洞 自由飞试验 发射装置 发射压力 发射速度 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程] V216.8