Modern aircraft with delta wings and small thickness ratios of inner fuselages often fly at high angles of attack, resulting in wing rock motion due to the lack of lateral damp, which seriously threaten the flight safety. A multidisciplinary numerical simulation method has been established to control the wing rock motion, integrating aerodynamics, flight mechanics and flight control characteristics. The active control progress of delta wing with trailing-edge control surfaces is investigated by solving unsteady Navier-Stokes equations on moving grids and rigid body motion functions with one degree of freedom under classical control laws. Furthermore, the kinetic characteristics of the controlled delta wing in different control states are analyzed. The numerical results indicate that the wing rock motion of the 80° sweep delta wing has been controlled effectively with the inlet Mach number of 0.3.
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