【作者】 汪球； 赵伟； 余西龙； 姜宗林；

【Author】 Wang Qiu;Zhao Wei;Yu Xi-long;Jiang Zong-lin;Institute of Mechanics,Chinese Academy of Sciences;

【机构】 中国科学院力学研究所；

【摘要】 高焓激波风洞作为能够模拟高超声速飞行条件总温的试验设备,具有研究高温真实气体效应的能力,是开展再入问题研究的有效地面设备,但是风洞试验时间较短,仅为毫秒量级,且试验结果数据曲线中夹杂着起动激波、驱动气体污染等信号,使得有效信号的分辨存在一定的难度,影响到最终实验结果的可靠性及精度,因此风洞有效试验时间段的确定是实验中必须解决的一道难题。本论文针对力学所JF-10高焓风洞上利用正向爆轰驱动方式获得的总焓16MJ/kg、总温7700K的高超声速试验气流状态,采用压力测量、静电探针测量、非接触光学测量、热流测量等多种方式,对比研究了风洞喷管的起动时间以及有效试验时间,试验结果表明:JF-10高焓风洞在上述状态下,喷管起动时间为~1.3ms,风洞有效试验时间为~2ms。更多还原

【Abstract】 The high enthalpy shock tunnel,which can provide the high temperature gas conditions for hypersonic flight,is an effective ground facility for the research of reentry problems.It also has the ability of studying real gas effect.However,the effective test time of a high enthalpy shock tunnel is short,in the order of milliseconds.In such a short time,the experimental test curve is mixed with starting shock wave and driver gas contamination signals,which makes it difficult to identify the effective signal part.Then the reliability and accuracy of the experiment result will be affected.Therefore,determination of the effective time for a high enthalpy shock tunnel is necessary.This paper is based on the JF-10 high enthalpy shock tunnel in the Institute of Mechanics.The hypersonic test flow condition with the stagnation enthalpy of 16MJ/kg and stagnation temperature of 7700 K is achieved using the forward detonation method.The experiments of pressure measurement,electrostatic probe,non-contact optical measurement and heat flux measurement are conducted.The nozzle starting time and effective test time is then studied through them.Results show that,under above test condition,the nozzle starting time of the JF-10 high enthalpy shock tunnel is about 1.3ms and effective test time is about 1.5ms.更多还原