Runway Debris Impact on Aircraft Composite Parts

The purpose in this paper is to investigate about the behavior of aeronautics composite material subjected to a low energy impact. Low velocity impact in aircraft composite panels is a matter of concern in modern aircraft and can be used either from maintenance accidents tools or in-flight impact with debris. The proposed study considers the dynamics of impact between a small piece of granular material and a large body of composite material. The principal aim is to simulate the impact of runway debris throw-up by the landing gear against an airplane structure. In this simulation, I want to investigate on CFRP composite panels affected by granular particles at low speed in theoretical and experimental tests. The finite element analysis, initially on the macroscale and subsequently on the microscale, shows the damage inside the composite according to the experimental results, but by itself, this classic numerical approach is little suitable to investigate the complete phenomenon. Developing the question, in first step by the classical approach, appears difficult on macro and microscale relationship besides their reciprocal influence over the deformation field. To resolve the last question, I will perform the first step on macroscale FEM analysis and then reduce from the size and effects over an opportune created RVE, such that microscale main effects as local delamination can be reproduced.

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Damage Tolerance of a Stiffened Composite Panel with an Access Cutout under Fatigue Loading and Validation Using FEM Analysis and Digital Image Correlation

Hiremath

Viswamurthy

Shettar

et al. 2022

Fibers

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Aircraft structures must be capable of performing their function throughout their design life while meeting safety objectives. Such structures may contain defects and/or damages that can occur for several reasons. Therefore, aircraft structures are inspected regularly and repaired if necessary. The concept of combining an inspection plan with knowledge of damage threats, damage growth rates, and residual strength is referred to as “damage-tolerant design” in the field of aircraft design. In the present study, we fabricated a composite panel with a cutout (which is generally found in the bottom skin of the wing) using a resin infusion process and studied the damage tolerance of a co-cured skin-stringer composite panel. The composite panel was subjected to low-velocity impact damage, and the extent of damage was studied based on non-destructive inspection techniques such as ultrasonic inspection. Fixtures were designed and fabricated to load the composite panel under static and fatigue loads. Finally, the panel was tested under tensile and fatigue loads (mini TWIST). Deformations and strains obtained from FE simulations were compared and verified against test data. Results show that the impact damages considered in this study did not alter the load path in the composite panel. Damage did not occur under the application of one block (10% life) of spectrum fatigue loads. The damage tolerance of the stiffened skin composite panel was demonstrated through test and analysis.

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Runway Debris Impact on Aircraft Composite Parts

Cited by 3 publications

References 7 publications

Numerical Simulation Approach for Low-Velocity Impact Response of Bioinspired Layup Design in GFRP Laminates

Numerical Simulation Approach for Low-Velocity Impact Response of Bioinspired Layup Design in GFRP Laminates

Multiscale Damage Modeling on Aeronautical Composite Under Low Energy Impact

Damage Tolerance of a Stiffened Composite Panel with an Access Cutout under Fatigue Loading and Validation Using FEM Analysis and Digital Image Correlation

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