2.4m跨声速风洞颤振试验流场控制技术研究  

Study on flow field control technique of flutter test in 2.4m transonic wind tunnel

作　　者：芮伟[1] 易凡[1] 杜宁[1] 秦建华[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2012年第6期83-86,共4页Journal of Experiments in Fluid Mechanics

基　　金：973项目'典型飞行器跨声速颤振特性研究'课题(61351)

摘　　要：颤振试验技术是研究飞行器颤振特性、评估安全飞行包络线的一项重要试验技术。为了满足颤振试验需要的定马赫数阶梯变速压和定总压线性变马赫数的试验要求,结合2.4m跨声速风洞的特点,有针对性地进行了控制策略设计。主要采用运动规律法和智能分段变PI实现变速压智能控制,应用运动函数实现了线性变马赫数智能控制。结果表明:该流场控制技术满足颤振试验的特殊要求,取得了流场调节过程快速、准确、可靠的试验效果。=Flutter test technique is an important test technique for studying the flutter charac- teristic of aircraft and evaluating the safety flight boundary of aircraft. In order to meet the re- quirements of adjusting dynamical pressure under constant Mach number and adjusting linear Mach number under constant total pressure in the flutter test in 2.4m wind tunnel, an intelligent control tactics of adjusting dynamical pressure was designed based on the law of motion and an in- telligent subsection PI, as adjusting linear Mach number based on motion function. It was proved that the application of the strategies mentioned above could satisfy the special requirements of flutter test, with which the flow field regulating effect in practical wind tunnel test was more swift, exact and reliable than ever.

关 键 词：颤振试验 变速压 运动规律法 线性变马赫数 运动函数 跨声速风洞 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]