Attitude-Elasticity-Aerodynamic Coupled Flutter Control Method for Flying Wing Aircraft

Abstract

The present invention discloses a method for attitude-elastic-aerodynamic coupled flutter control of an aircraft with a flying wing layout, which relates to technical fields such as mechanics, aeroelasticity, and control. The control method includes: integrating the Lagrangian equation in the general body axis system to establish a full-coupling dynamic model, and through small perturbation linearization, establishing a dynamic equation of perturbed motion for flight control system design; based on system identification flight tests, correcting the dynamic equation of perturbed motion; designing an attitude-elastic-aerodynamic coupled flutter suppression controller based on traditional or modern control theory and embedding it into the flight control system; verifying the effectiveness of the flutter suppression controller through flight tests. The present invention significantly solves the problems that existing numerical analysis and wind tunnel experiments cannot accurately reflect the complex coupling effects during flight, cannot effectively suppress the occurrence of flutter during flight, and cannot expand the flight envelope, etc., and can effectively improve the flight safety and stability of aircraft with a flying wing layout.