The Numerical Simulation of Non-linear Aeroservielasticity

摘要

By using unsteady aerodynamic solver, the wing’s unsteady loads can be solved directly in timedomain. The transfer function of the servo system in Laplace domain is transformed to the time domain toproduce the servo state equations. By solving the time domain aerodynamic equations, structure stateequations and servo state equations in every time step, the aeroservoelastic problem can be simulated intime domain. It can solve the aeroservoelastic problem with aerodynamic non-linearity easily, such astransonic, high angles of attack and hypersonic problem. By numerical simulation, the servo system cangreatly reduce the aeroelastic stability. The structural flitter added to the system can reduce the couplingeffect of servo system and structure mode and increase the flutter velocity.