Aeroservoelastic analysis for transonic missile based on computational fluid dynamics

The reduced order modeling (ROM) is constructed with the use of other methods including proper orthogonal decomposition (POD) technique and aerodynamic modeling based on the system identification technique. The ROM developed by using the system identification technique used to perform flutter studies at a high angle of attack and gust response analysis and transonic flutter suppression by active control. The open-loop aeroelastic results reveals the computational states that are M = 0.9, α = 0° and ρ = 1.0kg/m³. After constructing the open-loop aeroelastic model, the closed-loop model can be constructed by combining an open-loop aeroelastic system, a servo system, and the aerodynamic system of the control surface. For the closed-loop aeroelastic problem, feedback control is carried out by the additional aerodynamics produced by the active motion of the control surface. The closed-loop without a structural filter greatly changes the aeroelastic characteristics that are almost the same as the open-loop problem.