Abstract: Elastic missiles in atmosphere may have intense response due to gust e xcitation, which has great influence on structural safety, flight performance, a nd attack precision. Approaches of the calculations of aeroservoelastic response to the continuous and discrete gust for missiles were presented. The equations of motion considered the interaction of rigid-body modes and elastic vibration m odes, and the generalized aerodynamic forces were formulated in a way of quasi- s teady aerodynamics. The approach of the continuous gust response was based on the calculation of the power spectral density(PSD) using frequency-domain transfer functions. The approach of the discrete gust response was a time-domain integra l based on the state-space formulation of the aeroservoelastic system. An actual process of evaluating aeroservoelastic stability, calculating continuous and dis crete gust response, and modifying flight control system for a cruise missile wa s demonstrated. Numerical results indicate that adverse coupling between structu re and control system may deteriorate the stability and gust response of the sys tem. An appropriate structural notch filter in the control loop can effectively alleviate the adverse effects of elastic modes.