A calculation method of continuous gust aeroelastic response considering structural nonlinearity
The continuous gust aeroelastic response is generally analyzed and solved using random theory in engineering.By integrating the frequency response functions of the airplane with the power spectral density of excitation,the root mean square value of each degree of freedom can be obtained.The method is based on the linear solution in the frequency domain,and the nonlinear response analysis cannot be directly carried out.Therefore,based on the matched filter theory,a simplified calculation method for continuous gust response considering structure nonlinearity is described in this paper.By introducing a gust filter,which is connected in series to the aeroelastic dynamic system of the whole plane,a time-domain analysis model of continuous gust is obtained.Based on the root mean square value of the selected degrees of freedom,the matched filter theory is used to calculate a set of the"time correlated"response for the other degree of freedom.On this basis,for the nonlinear structure model,by adjusting the impulse strength amplitude,the maximum response is found as the nonlinear result,and finally a nonlinear continuous gust response calculation method suitable for engineering and structural nonlinearity is established.The simulated results showed that the method established in this paper can be used to obtain the"time-correlated"response of each degree of freedom,and can also be used for structural nonlinear response calculation.
万方数据
维普
