AEROSERVOELASTIC BEHAVIOR OF SUPERSONIC GUIDED FLIGHT VEHICLES

Flight dynamics of the guided vehicle is modelled by the aid of linear and angular equations of motions using Lagrange''s approach in this paper. Governing equations of the control system and the elastic behavior of the vehicle are added to the equations of dynamic states. Flexibility effect is modelled using the normal modes, generalized coordinates and forces. For validation of modified FORTRAN simulation code, the stability of specific vehicles is determined and compared with the same results in the literature. Using this code and by solving the governing equations for the desired flight vehicle, the aeroservoelasticity is analyzed and then the results are compared with the rigid cases and with the flight test data. Errors induced to control system sensors are shown in the figures. Good compatibility is achieved between the simulation and the experimental results. Fast Fourier transformations (FFT) is used for extracting the structural flexibility frequencies from the elastic simulation and flight test data.