Study of Aeroelastic Phenomena of the Hull and Thin-Walled Structures of Unmanned Aircraft at High Supersonic Speeds

Flutter of unmanned aircraft at hypersonic speeds is one of the understudied problems facing the designers of hypersonic vehicles. Modern methods for calculating aeroelastic stability either solve simplified versions of real problems (for example, without taking physicochemical phenomena into account) or require high computing power. This paper describes a methodology for calculating the supersonic and hypersonic flutter of an aircraft using standard engineering software and additionally developed software modules. The justification of the need to refine the existing methods for calculating the aircraft aeroelasticity taking into account the real geometry of the structure and with the possibility of accounting for physicochemical processes occurring in the air during the movement of bodies at high speed is provided. The theoretical principles of calculating aeroelastic stability taking into account these factors are developed, and three examples of calculating the aeroelastic stability of model objects are given.