空气动力学学报2019，Vol.37Issue(6)：999-1004,6.DOI:10.7638/kqdlxxbG2018.0151
2.4m跨声速风洞大振幅动态试验技术
Dynamic test technique with large amplitude in 2.4 m transonic wind tunnel
摘要
Abstract
During high maneuvering flight conditions of modern advanced flight vehicles,the coupled motion of mult﹣i degree﹣of﹣freedom would be induced.This behaviour presents the complex unsteady aerodynamic characteristics and mult﹣i degree﹣of﹣freedom motion attitudes.A two﹣degree﹣of﹣freedom pitch/roll coupled motion test device, which could be used for investigating high angle of attack static test,pitch oscillation,pitch﹣up in high speed and pitch/roll coupled oscillation,has been established for investigating and evaluating mult﹣i degree﹣of﹣freedom unsteady aerodynamic characteristics of advanced flight vehicles in FL﹣26 wind tunnel. The unsteady aerodynamic characteristics of one﹣degree﹣of﹣freedom motion and two﹣degree﹣of﹣freedom pitch/roll coupled oscillation for the typical 70﹣degree delta wing model are investigated based on the dynamic test devices.The results indicate that,the test data based on the dynamic test technique is reasonable and reliable which could represent the correct typical hysteresis characteristics of dynamic normal force and pitch moment.The test device is capable of measuring aerodynamic characteristics of two﹣degree﹣of﹣freedom pitch/roll coupled motion of advanced flight vehicles.This could provide technical support for the unsteady aerodynamic characteristics test evaluation and assessment of flight vehicles.关键词
动态气动力/大迎角/大振幅/双自由度/风洞试验Key words
dynamic aerodynamics/high angle of attack/large amplitude/two﹣degree﹣of﹣freedom/wind tunnel test分类
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马上,赵忠良,蒋明华,杨海泳,刘维亮,李玉平,王晓冰..2.4m跨声速风洞大振幅动态试验技术[J].空气动力学学报,2019,37(6):999-1004,6.基金项目
国家自然科学基金(11532016) （11532016）
