Dynamic aeroelastic subsonic discrete gust response analysis of lifting surfaces in time domain using Newark's method.

The Dynamic gust response analysis of lifting surfaces of aerospace structures requires attention to two main factors, namely, the character of the gust and the aeroelastic effects. In the present work,the Dynamic aeroelastic response of subsonic airplane in discrete gusts is determined using Newmark's direct integration method.The adopted time domain method is a departure from the usual modal analysis and the frequency domain approach.The aerodynamic strip theory is assumed,but compressibility and aspect ratio corrections may be included,if desired.The method has been validated by performing discrete gust response analysis of an airfoil model of the elastic wing flying through sharp-edged gust.The unsteady aerodynamic forces on the wing are calculated from the theory of two-dimensional thin airfoils in non-uniform motion.The theory takes proper account of 'unsteadiness' by using the kussner's and Wagner's unsteady lift functions for calculating the aerodynamic forces.The pitching motion and tail effects are neglected.For validating the present work,the responses obtained from Newmark's method is compared with those reported in literature using Laplace method.It is found that the results are in close agreement with reported in the literature

3rd National Conference on Image Processing, Computing, Communication, Networking and Data Analytics

This volume contains contributed articles presented in the conference NCICCNDA 2018, organized by the Department of Computer Science and Engineering, GSSS Institute of Engineering and Technology for Women, Mysore, Karnataka (India) on 28th April 2018