A Novel Design of a Pre-separation Panel Structure to Protect Against the Impact of an Explosion in an Aircraft Plenum Chamber

To reduce the damage of the pressurizing panel structure of a fuselage caused by an explosion at the“least risk bomb location”in an aircraft structure,a new pre-separation panel structure was designed to resist blast loading.First,the dynamic strain response and morphology of impact damage of the new pre-separation panel were measured in an impact damage test.Second,the commercial software LS-DYNA was used to calculate the propagation of the blast shock wave,and the results were compared with empirical equations to verify the rationality of the numerical calculation method.Finally,the fluid–structure coupling method was used to calculate the damage process of the pre-separation panel structure under the impact of an explosion wave and an impact block.The calculated results were in good agreement with the test results,which showed the rationality of the calculation method and the model.The residual strength of the damaged pre-separation panel was significantly higher than that of the original damaged panel.The results show that the new pre-separation panel structure is reasonable and has certain significance for guiding the design of plenum chambers with strong resistance to implosion for aircraft fuselages.

Design of aircraft structures against threat of bird strikes

In this paper, a method to design bird-strike-resistant aircraft structures is presented and illustrated through examples. The focus is on bird strike experiments and simulations. The explicit finite element software PAM-CRASH is employed to conduct bird strike simulations, and a coupled Smooth Particles Hydrodynamic（SPH） and Finite Element（FE） method is used to simulate the interaction between a bird and a target structure. The SPH method is explained, and an SPH bird model is established. Constitutive models for various structural materials, such as aluminum alloys, composite materials, honeycomb, and foam materials that are used in aircraft structures,are presented, and model parameters are identified by conducting various material tests. Good agreements between simulation results and experimental data suggest that the numerical model is capable of predicting the dynamic responses of various aircraft structures under a bird strike,and numerical simulation can be used as a tool to design bird-strike-resistant aircraft structures.

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.