Lateral dynamic characteristics analysis of elastic missile for controller design

In order to design the controller for cruise missile which will vibrate in flight, the lateral dynamic characteristics of the missile is analyzed in this paper. The intrinsic mode and aerodynamic parameters are calculated by using the software Nastran and Fluent. The additional unsteady aerodynamics caused by vibration is studied through simplified theory; the lateral rigid perturbation motion equations is established according to the linear theory respectively. The dynamic response of elastic vibration can be obtained after the additional unsteady aerodynamics loads are substituted to the perturbation motion equations as disturbance input. The results can provide initial data for stability analysis, precision analysis, guidance and control system design. The output response shows that the sideslip angle variation caused by elastic vibration will be very small, but the variation of bank angle will be significant, this result is matched with the experiment phenomenon. All the attitude angles are also vibrating with micro amplitude and high frequency, the adverse effects of vibration must be eliminated by the way of filtering or the other methods.