Aeroservoelastic analysis for supersonic and hypersonic missiles

Due to the difficulties in accurately calculating the aerodynamic forces and coupling the aeroelastic system with control system, it is always difficult to analyze the aerosen oelastic stability of missiles or airplanes accurately and efficiently. Based on local piston theory, this paper couples SISO control system with the aeroelastic system in state space and with this method, analyzes the aerosenoelastic problem of a typical missile as a computational example. The influences of Mach number, angle of attack, structural filter and location of sensor on aerosen oelastic characteristics are examined. The impact of control system on rigid and flexible bodies is also studied. Reasonable results are 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 aerosenoelastic characteristics for a missile or an airplane can be attained in a few minutes.