激波风洞超燃冲压发动机推力测量技术研究  

Research of scramjet thrust test in shock tunnel

作　　者：赵荣娟[1,2] 刘施然[1] 周正[2] 吴里银 吕治国[1] ZHAO Rongjuan;LIU Shiran;ZHOU Zheng;WU Liyin;LYU Zhiguo(Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 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,绵阳621000 [2]中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,绵阳621000

出　　处：《实验流体力学》2022年第4期103-108,共6页Journal of Experiments in Fluid Mechanics

基　　金：高超声速冲压发动机重点实验室基金(STS/MY-KFKT-2019004)。

摘　　要：为满足高马赫数超燃冲压发动机研制的需求,在激波风洞中开展了超燃冲压发动机推力测量技术研究工作,采用压电式推力测量天平测量了超燃冲压发动机模型上的推力。根据试验模型的受力特性进行了天平设计与校准研究,并在激波风洞中开展了验证性试验。在天平设计中,采用有限元力电耦合分析方法对天平性能进行了预估。分析结果表明:天平主分量的灵敏度可达到17.447 mV/N,一阶振动模态可达到1 022.40 Hz。在验证试验中,分别测量了超燃冲压发动机模型在喷注和不喷注燃料条件下的推力。试验结果表明:在2种试验状态下,发动机阻力差值最大约220 N,说明设计的压电式推力测量天平可分辨出不同试验条件下作用在发动机上的推力大小。In order to meet the need of high-Mach number scramjet development, the scramjet thrust test technique in the shock tunnel is studied. A piezoelectric balance is used to test the scramjet thrust in the shock tunnel. The research includes the balance design, calibration and thrust test in the shock tunnel. The finite element analysis method is used in the balance design to optimize the balance structure. The simulation results show that the sensitivity of the balance can reach 17.447 m V/N, and the first-order frequency mode can reach 1 022.40 Hz. The validation test is conducted in the shock tunnel with the fuel and without the fuel injection. The test results show that, the difference of the drag force is about 220 N between two different experimental conditions. Which means the thrust of the scramjet under different conditions can be distinguished with the new developed balance.

关 键 词：压电天平 超燃冲压发动机 推力测量 激波风洞 

分 类 号：TP204[自动化与计算机技术—检测技术与自动化装置]