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 windtunnel testing equipment for investigating the dynamics behaviour of a 3 degree of freedom (DoF) aeroelastic system. It is intended to incorporate a mechanical platform into the test section of an open-loop wind-tunnel for this purpose. This platform must be designed such that the desired aeroelastic phenomena, such as instability (flutter), occurs and can be observed within the operation regime of the wind tunnel. Hence, a string of numerical calculations and analysis must be conducted to determine the plaform parameters. Theoretical analysis needs to be carried out by first forming the system aeroelastic mathematical model. The model is derived from a 3 DoF mechanical system involving unsteady aerodynamics force and moment induced by the system dynamic response. The aerodynamic force is calculated using Doublet Point Method (DPM) by considering the wing section main modes. The obtained force then is combined with the system dynamic equations which further is transformed into a generalized coordinate system. By analyzing and simulating the mathematical model, the aeroelastic system parameters can be tuned to 'match' the wind-tunnel operation regime. Based on the obtained aeroelastic parameters, a platform configuration is designed and developed. The dynamic parameters of the platform must be adjusted such that they are equivalent to the mathematical model parameters. The dynamic characteristic of the platform then is evaluated and analyzed so that a compatible aeroelasticbehaviour can be observed during a wind-tunnel test.