Flutter analysis on hypersonic aircraft considering hysteresis nonlinearity
QUAN Weizhuo,FANG Mingxia(College of Aerospace Eng. & Mechanics,Tongji Univ.,Shanghai 200092,China)
To provide support for aircraft flutter control and structure design and so on,the free interface modal synthesis method of dynamic substructure method,which fits for complex structure modeling,is used to divide an aircraft into several substructures considering hypersonic flow and aircraft structure characteristics under supersonic flying condition;considering the actual working condition and manufacture technology of the connecting components between aircraft body and wings,the hysteresis nonlinearity effect generated by the interaction of occasional nonlinear effect and cubic nonlinear effect,and the effect of damping factor on the nonlinearity,a finite element software is used to calculate the parameters of dynamic characteristics and aerodynamic distribution of each substructures,the entire aircraft vibration differential equations are established,and the flutter characteristics are analyzed. The vibration,flutter characteristics and flutter critical situation are analyzed for the designed aircraft under the assumed condition. So the simulation and calculation on the aeroelastic problem of the entire aircraft is implemented. The analysis result indicates that the method can extend the calculation of hypersonic aircraft flutter issue and provide references for the application of dynamic substructure method on flutter study.