The Development of 3 DoF Wing Section Model for Aeroelastic and Active Control Wind Tunnel Experimental Tests

摘要

This paper discusses the development of a windtunneltesting equipment for investigating thedynamics behaviour of a 3 degree of freedom(DoF) aeroelastic system. It is intended toincorporate a mechanical platform into the testsection of an open-loop wind-tunnel for thispurpose. This platform must be designed suchthat the desired aeroelastic phenomena, such asinstability (flutter), occurs and can be observedwithin the operation regime of the wind tunnel.Hence, a string of numerical calculations andanalysis must be conducted to determine theplaform parameters. Theoretical analysis needsto be carried out by first forming the systemaeroelastic mathematical model. The model isderived from a 3 DoF mechanical systeminvolving unsteady aerodynamics force andmoment induced by the system dynamicresponse. The aerodynamic force is calculatedusing Doublet Point Method (DPM) byconsidering the wing section main modes. Theobtained force then is combined with the systemdynamic equations which further is transformedinto a generalized coordinate system. Byanalyzing and simulating the mathematicalmodel, the aeroelastic system parameters canbe tuned to 'match' the wind-tunnel operationregime. Based on the obtained aeroelasticparameters, a platform configuration isdesigned and developed. The dynamicparameters of the platform must be adjustedsuch that they are equivalent to themathematical model parameters. The dynamiccharacteristic of the platform then is evaluatedand analyzed so that a compatibleaeroelasticbehaviour can be observed during awind-tunnel test.