Modeling and analysis method of missiles considering the aeroelasticity

This article is mainly concerning about the dynamics modeling problems of big length-to-diameter ratio missile considering aeroelasticity. The vibration theory of bending beam was used to evaluate how the elastic deformation affects aerodynamic and force applied by thruster, considering both transverse and axial vibrations, based on the forces on rigid missile. Each additional force and moment was then derived so that all the forces and moments applied on flexible missile were obtained. Given the small perturbation assumption, linearization equations of motion were established and dynamic character analysis was carried out. Numerical simulation results show that high frequency vibration does not affect the stability of the system for vertical disturbances motion while low frequency one will cause system instability, and elastic vibration does not affect the stability of lateral disturbances movement. © 2013 TCCT, CAA.