An Experimental and Numerical Study of Bird Strike on a 2024 Aluminum Double Plate

This paper presents an experimentai and numerical study of the bird strike on a 2024-T3 aluminum double plate.The experiments are carried out at a desired impact velocity of 150 m/s.The explicit finite element software PAM-CRASH is used to Simulate the birdstrike experiments,and a coupled SPH-FE method is adopted,where the bird is modeled using the SPH method with the Mur naghan EOS and the struc ture is meshed with finite elemen ts.The mat erial parame ters are identified by an optimization process,and the Simula ted dynamic responses of bird strike are compared with experimentai measurements to verify the numerical model.The displacement and strain of the plate as well as the final deformation and damage show good agreemen t bet ween the simulation and the experimental resul ts.It suggests that the coupled SPH-FE met hod can provide an effec tive tool in designing bird-strike-resista nt aircraft component.

Effects of surface topography and specimen thickness on high-speed raindrop impact damage of CFRP laminates

Raindrop impact erosion has been observed since early days of aviation,and can be catastrophic for exposed materials during supersonic flight.A single impact waterjet apparatus is established for mimicking drop impacts at the velocities between 350 m/s and 620 m/s.Carbon Fiber Reinforced Polymer(CFRP)laminates with three different surface morphologies and specimen thicknesses are tested here.A central region with no visible damage has been noticed,surrounded by a"failure ring"with common damage patterns including resin removal,matrix cracking,fiber breakage and mass fiber loss.Asymmetric features are presented in the"failure ring"whose whole scope extends larger along the longitudinal direction than the transverse direction of the top layer.The mechanism of the resin removal is related to fiber-matrix debonding,and its onset and propagation can be facilitated by initial surface asperities with the shear action of the lateral jetting.In cases of multiple impact,good surface quality can slow down the evolution of resin removal and fiber exposure on the CFRP surface,reducing the erosion speed and delaying the occurrence of structural damages in the subsequent impacts.Rayleigh wave dominates the occurrence of matrix cracking on the CFRP surface,and subsequently,results in material loss and peeling of the top-layer because of lateral flow.With the increase of the specimen thickness,both the interlaminar and intralaminar failures decrease as the impact damage mechanism changes from plate bending stress to the reflection of stress waves.

Numerical simulation of a UAV impacting engine fan blades

A 3D digital model of a small Unmanned Aerial Vehicle(UAV)is obtained by using the method of scanning reverse modeling and joint mapping.A numerical simulation of a small UAV strikes on rotary engine blades,presented in this paper,was performed with a Transient Nonlinear Finite Element code PAM-CRASH software.A test of motor strike on plate was developed and the dynamic response of the plate were obtained to validate the numerical simulation method of a UAV strike on blades.Based on this,dynamic damage response caused by UAV on the engine blades were studied.It is indicated that the impact process between the UAV and a single blade can be divided into two typical stages:cutting and impact.Cutting mainly leads to the failure of the leading edge material,and impact mainly leads to the plastic deformation of the blade.At the same time,it is compared with the damage impacted by bird with the same mass.For the same mass of bird and UAV,the damage caused by UAV striking fan blade is more serious,and 1.345 kg UAV striking fan blade of typical civil aviation engine is enough to cause damage to flight safety.