展望系统辨识方法在大攻角气动问题研究中的应用

在分析了目前进行飞行器大攻角气动特性研究所采用的尾旋风洞试验、常规风洞自由飞试验和遥控模型自由飞试验的优缺点之基础上指出:把系统辨识方法与这些试验方法结合起来,是一种行之有效的研究飞行器大攻角气动问题的技术途径,它可以简化这些试验方法的一些技术环节,提高试验精度。若气动数据来源于尾旋风洞,这种新方法只能研究飞机的发展尾旋和改出尾旋;若气动数据来源于常规风洞,这种新方法也只能研究飞行器的大攻角、偏离、过失速和失速性滚摆/滚转模态;只有通过模型自由飞获取气动数据,这种新方法才有可能研究包括尾旋全过程在内的各种大攻角飞行模态。

PROSPECTS FOR THE APPLICATION OF SYSTEM IDENTIFICATION METHOD IN THE STUDY OF AERODYNAMIC PROBLEMS AT HIGH ANGLE OF ATTACK

The advantages and disadvantages of spin wind tunneltest,conventional wind tunnel free-flight test and radio-controlled modelfree-flight test usually used to study the aerodynamic characteristics ofvehicles at high angle of attack today are analyzed in this papar.Basedon the analysis above,it is pointed out that combining the systemidentification method and these test methods is an effective technologicalapproach to study the aerodynamic characteristics of vehicles at highangle of attack,it simplifies some links of these tests and improvesthe test accuracy.Nevertheless,if the aerodynamic derivatives comefrom spin wind tunnel test,the new method can only study developedspin and recovery from aspin;if the aerodynamic derivatives come fromconventional wind tunnel test,the new method can only study the modesof airplane at high angle of attack,departure,post-stall,stalled wingrock and rolling modes:only when the aerodynamic derivatives are gainedby means of radio-controlled model free-flight test,the new methodcan study all flight modes at high angle of attack including the wholespin process.