Aeroservoelastic analysis method for supersonic missiles based on local piston theory

It is always difficult to analyze the aeroservoelastic stability of missiles or airplanes accurately and efficiently. The difficulty comes from two aspects: to calculate the aerodynamic forces accurately and efficiently, and couple the aeroelastic system with control system. Based on local piston theory, this paper coupled SISO control system with the aeroelastic system in the state space. Aeroservoelastic problem of a typical missile was analyzed with this method as the computational example. The influences of Mach number, angle of attack, structural filter and location of sensor on aeroservoelastic characteristics were examined. The impact of control system on rigid and flexible bodies was also studied. Reasonable results were attained in the conditions of Mach number between 1.2 and 10, angle of attack up to 10 degrees. Results given by this method accorded with those given by theory analyses. With this method, the analysis of the aeroservoelastic characteristics for a missile or an airplane can be attained in a few minutes.