| The motion of modern aircraft is mainly controlled by the flight control system.When the flight control system drives the rudder to deflect,the rudder feeds back the high-frequency signals caused by structural elastic vibration of aircraft.This additional high-frequency excitation results in a further elastic vibration of the structure.With the coupling of aerodynamic/structural dynamic/control system,the design of the aircraft encounters new aeroelastic problems.In the aircraft design process,the aeroelasticity of the interaction between the elastic vehicle and the control system must also be considered and the control system should not be ignored.In the thesis,the numerical coupling method of CFD/CSD with motion and control system is investigated for dealing with the problems of aircraft aeroelasticity in maneuvering state.First of all,the numerical methods for solving flow governed equations are introduced,which contains spatial discretization method,temporal discretization method,boundary conditions and turbulence mode.Then the numerical simulation method of aeroelasticity is introduced.The linear modal superposition method is used to solve the structural dynamic equation.Mesh Deformation is achieved by Delaunay graph map.The exchange of information between CFD grid and structural grid is achieved by infinite plate spline and constant volume tetrahedron.Modified loose coupling method is used in CFD/CSD Coupling.Then the numerical simulation method of aeroelastic response of aircraft in maneuvering flight is developed by coupling with computational fluid dynamics,computational structural dynamics and control equations.The relative motion of the components of the aircraft is achieved by overlapped grid,and the motion of rigid body is processed by six-degree-of-freedom equations.Finally,the aeroelastic response of an aircraft during maneuver flight is analyzed by using the numerical method proposed in this thesis and the results show that the method is efficient and useful. |
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