Effect of Impact and Bearing Parameters on Bird Strike with Aero-Engine Fan Blades

Bird strikes are one major accident for aircraft engines and can inflict heavy casualties and economic losses. In this study, a smoothed particle hydrodynamics (SPH) mallard model has been used to simulate bird impact to rotary aero-engine fan blades. The simulations were performed using the finite element method (FEM) at LS-DYNA. The reliability of the material model and numerical method was verified by comparing the numerical results with Wilberk’s experimental results. The effects of impact and bearing parameters, including bird impact location, bird impact orientation, initial bird velocity, fan rotational speeds, stiffness of the bearing, and the damping of the bearing on the bird impact to aero-engine fan blade are studied and discussed. The results show that both the impact location and bird orientation have significant effects on the bird strike results. Bird impact to blade roots is the most dangerous scenario causing the impact force to reach 390 kN. The most dangerous orientation is the case where the bird’s head is tilted 45° horizontally, which leads to huge fan kinetic energy loss as high as 64.73 kJ. The bird’s initial velocity affects blade deformations. The von Mises stress during the bird strike process can reach 1238 MPa for an initial bird velocity of 225 m/s. The fan’s rotational speed and the bearing stiffness affect the rotor stability significantly. The value of bearing damping has little effect on the bird strike process. This paper gives an idea of how to evaluate the strength of fan blades in the design period.

Investigate the Crashworthiness of high-velocity bird impact on three different designed model wings by using Coupled Eulerian-Lagrangian approach

Bird strike is a significant threat to the parts of the flying aircrafts. The wing is a central part, which provides stability to the aircraft. Mostly at wing, bird attack the leading edge. Worldwide aviation regulation FRA, EASA, required 4Ib bird strike on the wing of aircraft, and after this bird strike, aircraft is able to be safely landed. This study aims to investigate the resistance of the wing against the bird strike and damage analysis of the high-velocity bird collision on the model wing, inner structure, spar, and ribs. By using the Coupled Eulerian-Lagrangian (CEL) approach in ABAQUS/Explicit. Our contribution 1) bird strike on a wing with assembled inner structure by aluminium and outer skin composed of unidirectional fiber-reinforced composite material. 2) bird strike on-wing which is similar with the first test in which the difference is of spar designed layers of horizontal plates like a comb. 3) bird strike on-wing which is similar with second model wing difference in this wing put an aluminium leading edge on the skin leading-edge, final to analyze the damage of bird impact on the wing, the velocity of bird strike is 200m/s and analyze the behavior of the bird at this velocity. Resistance behavior of composite skin After penetration in the wing, analyze the impact on the spar and stress on the inner structure. Analysis of the kinetic and internal energy graph and Comparison all of these results and check the performance, which gives an excellent result at this velocity. based on these results suggest which inner part is sensitive.

Verification and application of bird strike analysis for the design of high-speed helicopter composite cowlings

Bird strikes are an important phenomenon that must be taken into consideration when designing aircraft. A bird impact experiment provides a direct method to examine the bird strike resistance. However, the design of the aircraft structures usually involves many iterations of design-manufacturing-test and conducting bird impact experiments is not only time consuming but also costly. The aim of this work is to show the application of test verified numerical simulation for the design of composite cowlings of the high-speed helicopter.

INFLUENCE OF A BIRD MODEL SHAPE ON THE BIRD IMPACT PARAMETERS

One of the factors which significantly exert a negative influence on flight safety is a collision of an aircraft with birds. Various parts of an aircraft are subjected to damage. Within the conducted analyses, the impact loaded object was a helicopter windshield. Apart from the mandatory physical tests, there are various numerical methods for bird strike modeling. Among them, in this paper, the Smooth Particle Hydrodynamics (SPH) is being used and developed for bird modeling. Investigations exploit various geometric figures in order to model the bird shape. Few authors present research findings which employ an approximate shape of certain bird species. For comparison three bird models were elaborated upon, one in the shape of a cylinder with hemispherical ends (homogeneous model) and two others as multi-material models, one in the shape of a simplified white stork and the other one close to the real-life white stork. Multi-material bird models had various parameters. It must be noted that the maximum value of the resultant windshield displacement varies for different bird models. The bird model close to the real-life white stork caused the smallest deflection, while the bird model in the shape of a simplified white stork and the homogeneous bird model led to the biggest damage, respectively. It is important to add that the models are of the same mass, impact velocity and a different size. This has an impact on the kinetic energy distribution during the collision process, which results in different windshield bending values.

Investigate the Crashworthiness of high-velocity bird impact on three different designed model wings by using Coupled Eulerian-Lagrangian approach

Bird strike is a significant threat to the parts of the flying aircrafts. The wing is a central part, which provides stability to the aircraft. Mostly at wing, bird attack the leading edge. Worldwide aviation regulation FRA, EASA, required 4Ib bird strike on the wing of aircraft, and after this bird strike, aircraft is able to be safely landed. This study aims to investigate the resistance of the wing against the bird strike and damage analysis of the high-velocity bird collision on the model wing, inner structure, spar, and ribs. By using the Coupled Eulerian-Lagrangian (CEL) approach in ABAQUS/Explicit. Our contribution 1) bird strike on a wing with assembled inner structure by aluminium and outer skin composed of unidirectional fiber-reinforced composite material. 2) bird strike on-wing which is similar with the first test in which the difference is of spar designed layers of horizontal plates like a comb. 3) bird strike on-wing which is similar with second model wing difference in this wing put an aluminium leading edge on the skin leading-edge, final to analyze the damage of bird impact on the wing, the velocity of bird strike is 200m/s and analyze the behavior of the bird at this velocity. Resistance behavior of composite skin After penetration in the wing, analyze the impact on the spar and stress on the inner structure. Analysis of the kinetic and internal energy graph and Comparison all of these results and check the performance, which gives an excellent result at this velocity. based on these results suggest which inner part is sensitive.