Research On The Static And Dynamic Buckling Of The Composite Honeycomb Structure In The Out-of-plane Direction

The composite honeycomb is a novel kind of material which is made of carton fiber composite laminate instead of aluminum foil.This kind of honeycomb is lower in density and higher in stiffness and strength,able to solve the electric corrosion problem when combining the aluminum honeycomb with the carton fiber composite panels.Meanwhile, As It’s environmentally friendly and easy recycled,the composite honeycomb is promising to take the place of aluminum honeycomb to be the major structural material in the aerospace.In the recent years,honeycomb has gradually been used in the field of vessel,vehicle,bridge and architecture.That the composite honeycomb structures being used in the deck and superstructure can greatly reduce the weight and improve the flexibility of the warships.So it’s necessary to take research of this novel kind of honeycomb.This paper mainly study both the static and dynamic buckling character of the honeycomb in the out-of-plane direction.Research into the static buckling character of the composite honeycomb in the out-of-plane direction would mainly use both the theoretical analysis method and FEA method.The theoretical analysis is basing on the classic composite laminate buckling theory.Three different boundary condition assumptions associated with the horizontal lines of the honeycomb wall had been introduced into the model.Both the boundary constraint equations and static buckling control differential equations are combined and solved by the single series method.The dimensionless method was used to discuss the influence of the structure size to the static critical buckling load of the honeycomb.The FEA simulation had simplified the infinite and periodic boundary condition of the honeycomb,and builded up the three dimensional FEA geometric model with proper boundary constraint.The initial buckling load of different honeycombs had been computed,and the influence of the honeycomb material, size,and composite stacking sequence had been discussed.On the other hand,research into the dynamic buckling character of the composite honeycomb in the out-of-plane direction would mainly use the method of explicit dynamics analysis.In the common FEA software,the simulation had simplified the infinite and periodic boundary condition of the honeycomb and builded up the three dimensional FEA geometric model with proper boundary constraint. A total of four kinds of impact load styles as rectangular pulse load,ramp pulse load,reverse ramp pulse load and triangle pulse load. The Hashin composite failure criterion had been introduced to model the failure in the composite during the impaction.In the post-processing,the displacement-time curves of the feather points had been plotted,and the B-R method was used to determine the initial dynamic buckling time and load.Parametric and dimensionless discuss about the influence of the thickness,aspect ratio,intersection angle of the honeycomb and impact time and load to the dynamic buckling response.This research is meaningful to the static and dynamic buckling design of the composite honeycomb in the future.