一种超声速气动发电机实验装置及实验技术研究  

Studies on Experimental Equipments and Testing Technology of Gas Dynamotor

作　　者：陈志敏[1] 于昆龙 

机构地区：[1]西北工业大学航空学院流体力学系,西安710072 [2]中国空气动力研究发展中心,绵阳621000

出　　处：《实验力学》2004年第3期386-390,共5页Journal of Experimental Mechanics

摘　　要：在对超声速榴弹炮以及导弹引信供电系统的发电机研究中,过去常在闭口式风洞进行实验,但由于闭口式风洞中各种相似参数和特有的因素影响,使得实验数据与真实飞行数据完全不符。因此,多年来只得靠实弹打靶来完善设计方案。本文利用气体动力学和实验空气动力学理论,设计了一种适合气动发电机的超声速试验射流装置,并通过试验详细地研究了装置在出口的流场品质和不同几何外形气动发电机的转速特性,给出了合理的模型试验区、喷管出口流速的确定方法和射流实验区参考压力的选取方法,最后对模型实验结果与打靶遥测数据进行了对照。研究表明,利用超声速射流的工作原理进行导弹引信发电机的模拟实验是可行的,并且该装置可用于引信产品验收。The close-stomata wind tunnel experiments have been generally used for studying supersonic projectile, missile as well as dynamotor of missile fuze power supply system. However the obtained data entirely didn′t agree with those from the true flight due to the effect of similitude parameters and special factors in wind tunnel. Therefore, There was no alternative but to take target practice in order to consummate design project in the past. In this work, based on the gas dynamics and experimental aerodynamics, a kind of supersonic test jet equipment, which suits for aerodynamic dynamotor was designed. The flow field character at exit of jet wind tunnel and the rotating speed characteristic of aerodynamic dynamotor with different geometry figures were tested for the equipment. The reasonable model test section, the method of confirming exit speed at nozzle and the technique of selecting reference pressure at jet test section are proposed. The data from the model experiments and the distant measurement of target practice are compared. The results indicates that it is possible to perform simulation experiments of missile fuze dynamotor in virtue of supersonic jet theory, and this equipment can be used for checking and accepting fuze production.

关 键 词：超声速 引信 射流装置 实验空气动力学 遥测数据 导弹 喷管 几何 实验装置 实验区 

分 类 号：O358[理学—流体力学] V211[理学—力学]