In this research the post-impact behaviour of composite fuselage panels subjected to single and multi-site, high and low-velocity impacts is investigated.

Our models consist of multi-step analyses simulating the impacts and the compression after impact. The models use:

  • Physically based failure models
  • Advanced contact algorithms
  • A damping step after each impact step
  • A compression step after the vibrations due to the impact have stopped.

Both single and multiple impacts have been modelled on large scale composite panels followed by compression after impact to failure. Various impact scenarios (location and energy) are simulated according to probable impact energies (mass and velocity) on a regional aircraft fuselage.