The formulation and general scheme of solving the problem of joint design of the structure and automatic control system (ACS) of a maneuverable unmanned aerial vehicle (UAV), taking into account the requirements of aeroelasticity, are given. The tasks of ensuring safety from flutter and aeroelastic stability of UAVs with self-propelled guns in the process of designing an aircraft are solved using calculation, calculation and experimental and experimental methods. The presented methods relate primarily to guided UAVs (guided missile in foreign literature) of the air-to-air, air-to-surface and partly surface-to-air classes, for which the problems of flutter and dangerous aeroelastic self-oscillations are extremely important.