Modeling And Simulation Of Boundary Problems Subjected To Separating Impact

The airborne missile launch undergoes a complex dynamic process, with complicated joints and boundaries among the missile. There are all kinds of connecting ways, in which complex problems exist, such as nonlinear, uncertainty and variability, so the research of the dynamic problems has larger challenge. so it's always a hotspot of research to use system response signal that can be often get more easily to identify joints, concerned by the world's aerospace fields and vibration engineering domain.At present, the basic theories and methods of study about the piece whose structure is single or the partial strength and stability of a piece has been quite mature. In this paper, aiming to the separating impact condition, the rigid-flexible dynamic modeling of the joints between the missile-launcher and the launching taxiing is observed, which overcomes past static modeling and analysis. Use of secondary development to achieve the boundary conditions simulation. The vibration analysis is implemented based on the software MSC.ADAMS/Vibration, thereby avoiding the actual test only in the design of the late and costly defects. The impact of the stiffness and the damping of the system joints under the low-frequency vibration on the frequency response are studied.Based on "a Gaussian white noise inspired by the nonlinear dynamic equations can solve equations counterparts in the FPK be accurate steady-state solution. ", missile sliding the first order nonlinear dynamics equations containing joints are established to identify stiffness coefficient by solving the steady-state solution of the corresponding FPK equation, based on the relationship between nonlinear restoring force and probability density. Simulation shows that the method can better identify connection parameters of the structure of nonlinear systems.