ABSTRACT
The titanium honeycomb core structures are gradually used in several modern aircrafts recently in China. In the manufacturing process and service, low velocity impacts from foreign objects would quite likely happen and could not be avoided. This chapter introduces the experimental and numerical study on the performance of titanium honeycomb core structures with low-velocity impact damage subject to uniaxial compression. In the manufacturing process and service, low velocity impacts from foreign objects would quite likely happen. A parametric finite element model for the full size titanium honeycomb sandwich panel with low velocity impact damage was generated automatically in ABAQUS by using a code developed in Python. For the panel without impact damage, under the increasing compressive load, the face sheet close to the end of the panel would buckle first, then lead to the collapse in the honeycomb core nearby and finally cause the catastrophic failure of the panel.
