Identification of aircraft longitudinal aerodynamic parameters using an online corrective test for wind tunnel virtual flight  

作　　者：Shang TAI Chen BU Yanling WANG Ting YUE Hailiang LIU Lixin WANG 

机构地区：[1]School of Aeronautical Science and Engineering,Beihang University,Beijing 100191,China [2]AVIC Aerodynamics Research Institute,Harbin 150001,China

出　　处：《Chinese Journal of Aeronautics》2024年第9期261-275,共15页中国航空学报（英文版）

摘　　要：The identification of aerodynamic parameters is accomplished through the test data of the dynamic movement of scaled aircraft models flying dynamically in wind tunnel,which can real-ize the accurate acquisition of the aerodynamic model of the aircraft in the preliminary stage for aircraft design,and it is of great significance for improving the efficiency of aircraft design.How-ever,the translational motion of the test model in the wind tunnel virtual flight is subject to con-straints that result in distinct flight dynamics compared to free flight.These constraints have implications for the accuracy of aerodynamic derivatives obtained through the identification of wind tunnel test data.With this issue in mind,the research studies the differences in longitudinal dynamic characteristics between unconstrained free flight and wind tunnel virtual flight,and inno-vatively proposes an online correction test based wind tunnel virtual flight test technique.The lon-gitudinal trajectory and velocity changes of the model are solved online by the aerodynamic forces measured during the test,and then the coupled relationship between aircraft translation and rota-tion is used to correct the model's pitch attitude motion online.For the first time,the problem of solving the data approximation for free flight has been solved,eliminating the difference between the dynamics of wind tunnel virtual flight and free flight,and improving the accuracy of the aero-dynamic derivative identification results.The experiment's findings show that accurate aerodynamic derivatives can be identified based on the online correction test data,and the observed behaviour of the identified motion model has similarities to that of the free flight motion model.

关 键 词：Wind tunnels Displacement constraints Online solution Flightcontrol law Aerodynamic parameter identification 

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]