FE analysis of geometry effects of an artificial bird striking an aeroengine fan blade
TL;DR: In this article, the impact behavior of an artificial bird impinging a flexible aeroengine fan blade was analyzed using the LS-DYNA simulation model and the results showed that the initial contact area between the bird and target in the early phase of the impact event would have a significant effect on the peak impact force.
About: This article is published in International Journal of Impact Engineering.The article was published on 2008-06-01. It has received 117 citations till now. The article focuses on the topics: Bird strike.
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TL;DR: An overview on the development, characteristics and applications of different soft body impactor modeling methods by an extensive literature survey is given, which highlights the advantages and disadvantages of the most established techniques.
191 citations
TL;DR: In this paper, experiments of bird impact with a flat plate are conducted at different striking velocities and simulated using an explicit finite element software PAM-CRASH with three bird material models.
70 citations
TL;DR: In this paper, a bird model with geometry similar to a real bird (Bufflehead Duck) is introduced and compared to traditional bird models and also to experimental data. But, since all birds do not have the same body shapes and sizes, and since it is not always convenient to model a complex bird body, four substitute bird models are introduced.
62 citations
TL;DR: In this paper, the authors provide an overview of the literature dealing with three types of soft impacts of concern for the aerospace applications, namely impacts of rain drops, hailstones and birds against aircraft.
56 citations
TL;DR: Two different Modified multi-extremum Response Surface basis Models (MRSM) are proposed for dynamic nonlinear responses of failure capacities for turbine blisk responses and the predicted results showed that the sensitivity analysis based on MRSM accurately provided the effective degree for input variables.
Abstract: For the nonlinear dynamic analyses of complex mechanical components, it is necessary to apply efficient modeling framework to reduce computational burden. The accurate surrogate model for approximating the nonlinear responses of several failures is a vital issue to provide robust and safe design conditions in complex engineering applications. In this paper, two different Modified multi-extremum Response Surface basis Models (MRSM) are proposed for dynamic nonlinear responses of failure capacities for turbine blisk responses. The proposed MRSM is established using two regression processes including regressed the input variables by linear or exponential basis functions in first calibrating phase and regressed the second-order polynomial basis function using inputs data provided by first stage in second calibrating procedure. A sensitivity analysis using MRSM is proposed to consider the variation of input variables on the nonlinear responses. In the sensitivity analysis procedure, the effects of input variables are evaluated using the calibrating results given from the first regressed process. To evaluate the performance of the proposed MRSM, three multi-extremum failure modes including radial deformation of compressor blisk, maximum strain, and stress of compressor blade and disk are considered. the prediction of MRSM of nonlinear responses for Thermal-fluid–structure system with dynamical nonlinear finite-element analyses is compared with response surface method (RSM) and artificial neural network (ANN). The predicted results of modeling approaches showed that the sensitivity analysis based on MRSM accurately provided the effective degree for input variables. The gas temperature has the highest effects on nonlinear responses of turbine blisk which is followed by angular speed and material density. The MRSM combined with basic exponential function performs better than other models, while the MRSM coupled with linear function is more accurate than ANN and RSM. The proposed MRSM models have illustrated the accurate and efficient framework for approximating dynamic structural analysis of complex components.
55 citations
References
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16 Apr 1993
TL;DR: In this article, failure in ductile material using finite element methods and modelling the process of failure in structures are discussed. But the authors focus on the inelastic rupture of ductile metal beams subjected to large dynamic loads, strain localisation and fracture in metal sheets and thin walled structures; impact on metal tubes; indentation and perforation; composite strength and energy adsorption as an aspect of structural crash resistance; crash response of composite structures; dynamic compression of cellular structures and materials; elastic effects in the dynamic plastic response of structure; impact performance of aluminium structures
Abstract: : Failure in ductile material using finite element methods; modelling the process of failure in structures; criteria for the inelastic rupture of ductile metal beams subjected to large dynamic loads; strain localisation and fracture in metal sheets and thin walled structures; impact on metal tubes; indentation and perforation; composite strength and energy adsorption as an aspect of structural crash resistance; crash response of composite structures; dynamic compression of cellular structures and materials; elastic effects in the dynamic plastic response of structure; impact performance of aluminium structures, motorway impact attenuation devices: past, present and future; and grounding damage of ships
211 citations
TL;DR: In this article, a finite element model is developed for simulating the bird strike tests, using Smooth Particle Hydrodynamics (SPH) for modelling the bird and the material model developed in Part 1 of the paper for modeling the leading edge skin.
Abstract: Fibre Metal Laminates with layers of aluminium alloy and high strength glass fibre composite have been reported to possess excellent impact properties and be suitable for aircraft parts likely to be subjected to impacts such as runway debris or bird strikes. In a collaborative research project, aircraft wing leading edge structures with a glass-based FML skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. In this second part of a two-part paper, a finite element model is developed for simulating the bird strike tests, using Smooth Particle Hydrodynamics (SPH) for modelling the bird and the material model developed in Part 1 of the paper for modelling the leading edge skin. The bird parameters are obtained from a system identification analysis of strikes on flat plates. Pre-test simulations correctly predicted that the bird did not penetrate the leading edge skin, and correctly forecast that one FML lay-up would deform more than the other. Post test simulations included a model of the structure supporting the test article, and the predicted loads transferred to the supporting structure were in good agreement with the experimental values. The SPH bird model showed no signs of instability and correctly modelled the break-up of the bird into particles. The rivets connecting the skin to the ribs were found to have a profound effect on the performance of the structure.
160 citations
01 Jul 1978
TL;DR: An unsteady, hydrodynamic model of the impact of a low strength projectile on a rigid or semi-rigid target has been developed and impact tests of various materials including birds, gelatin, and RTV rubber have been conducted to validate this theory.
Abstract: : An unsteady, hydrodynamic model of the impact of a low strength projectile on a rigid or semi-rigid target has been developed. Impact tests of various materials including birds, gelatin, and RTV rubber have been conducted to validate this theory. At velocities above 100 m/s, these materials were seen to flow as a fluid upon impact. The resulting impact pressure histories were very similar to those predicted using the model. The impact process was dominated by an initial shock phase which was quickly followed by a release to a steady flow condition. This model should be applicable to the impact of any material for which the shock pressures generated during impact are much greater than the strength of the projectile but are less than the strength of the target. (Author)
150 citations
TL;DR: In this paper, a Lagrangian approach is adopted, interfacing the ESI/Pam-Crash solver code with an automatic trial-and-error procedure for the elimination of the excessively distorted elements.
120 citations
TL;DR: A comprehensive program was conducted to develop a model synthetic bird for use in engine blade impact testing and it was determined that a projectile fabricated from commercial gelatin impregnated with phenolic mircoballoons most nearly duplicated the impact loading history of real birds.
Abstract: A comprehensive program was conducted to develop a model synthetic bird for use in engine blade impact testing. A hydrodynamic theory of the impact event was used to aid in determining the bird properties which had to be duplicated in the model. Of the two candidate models studied extensively, it was determined that a projectile fabricated from commercial gelatin impregnated with phenolic mircoballoons most nearly duplicated the impact loading history of real birds.
100 citations