Integrative simulation technique of coupled aerodynamics and flight dynamics with control law on a vehicle

A method based on unstructured overset grid and global sub-iteration is developed, which is used to investigate the virtual flight of a vehicle with closed-loop control by synchronously simulating the coupled aerodynamics and flight dynamics. A static instable hypersonic configuration is pulled up with an increasing attack angle and then trimmed at a certain attack angle according to the designed control law, which is performed by the elevator deflection. The numerical virtual flight presents such integrative evolvement of unsteady flow, rigid body movement and aerodynamic control surfaces vividly. The numerical virtual flight agrees well with the traditional flight simulation based on aerodynamic database in terms of control effects, while there exits some difference during the whole process.