连续式风洞二喉道调节马赫数控制策略  

Mach number control strategy for continuous wind tunnel with second throat

作　　者：陈旦[1] 张永双 李刚[1] 郭守春[1] 陈天毅[1] CHEN Dan;ZHANG Yongshuang;LI Gang;GUO Shouchun;CHEN Tianyi(Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China;School of Automation Engineering,University of Electronic Science and Technology of China,Chengdu 611731,China;Key Laboratory for Wind Engineering of Sichuan Province,Southwest Jiaotong University,Chengdu 610031,China)

机构地区：[1]中国空气动力研究与发展中心设备设计及测试技术研究所,四川绵阳621000 [2]电子科技大学自动化工程学院,成都611731 [3]西南交通大学风工程四川省重点实验室,成都610031

出　　处：《航空动力学报》2019年第10期2167-2176,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(11602292,61801479)

摘　　要：为了降低连续式跨超声速风洞压力波动,提高马赫数稳定性,需要对二喉道调节马赫数控制方式进行研究,针对现有文献鲜少对该控制策略描述等问题,以0.6m连续式跨声速风洞为例,对二喉道控制马赫数的原理进行分析,基于运动控制器加伺服驱动器双PID(proportion-integral-derivative)控制模式实现二喉道位置精确控制,提出了二喉道和压缩机转速的组合控制流程,并采用分段变参数模糊PID加串级控制的算法实现马赫数精确控制,最后进行了试验验证。结果表明马赫数控制精度优于0.001,且每个马赫数极曲线(9个攻角阶梯)的时间可控制在4min以内,证明所提出的控制策略是有效的,可为连续式跨超声速风洞的设计调试提供参考。In order to reduce pressure fluctuation and improve Mach number stability in continuous trans-supersonic wind tunnel,it is necessary to study the Mach number control model of second throat.In view of the few descriptions involved in existing literature,taking 0.6 mcontinuous transonic wind tunnel as an example,the principle of the Mach number control with second throat was analysed,then the precise position control of second throat was realized based on the double PID(proportion-integral-derivative)control mode of motion controller plus servo driver,and the combined control sequence of second throat and compressor speed was presented,and then the algorithm of segmented variable parameter fuzzy PID and cascade control was proposed to control the Mach number.Finally,experiments were carried out.The results show that the Mach number control accuracy can be better than 0.001,and the time of each Mach number polar curve(9 attack angles)can be controlled within 4 minutes,proving that the control strategy proposed is effective,and can provide reference for the design and construction of continuous trans-supersonic wind tunnel.

关 键 词：连续式跨超声速风洞 马赫数控制 二喉道 分段变参数模糊PID 串级控制 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]