Smooth Particle Hydrodynamics Birdstrike Analysis on Aircraft Wing Leading Edge

Hampson, Paul; Talhah, Imran

Abstract

Aircraft wing leading edges subjected to simulated birdstrike impact was investigated using the finite element ANSYS Autodyn solver. The bird was modelled using a Smooth Particle Hydrodynamics (SPH) method. Two validation studies were conducted prior to the main investigation. The first simulated impact on aluminium panels of varying thicknesses and impact velocities with results compared to Cessna Aircraft Company test data and a study conducted using LS-Dyna. The second validation study was performed on a steel plate at various impact velocities with results compared to U.S. Naval Research Laboratory data and a LS-Dyna solution. Following the validation studies, bird impact was simulated on aluminium and carbon fibre composite wing skin leading edges. Various skin thicknesses were investigated at an impact velocity of 155m/s (300 knots). Leading edge displacement and stress results showed that the carbon fibre composite material had a greater resistance than the aluminium to withstanding the high-speed impact.

Citation

Hampson, P., & Talhah, I. (2021). Smooth Particle Hydrodynamics Birdstrike Analysis on Aircraft Wing Leading Edge. International Journal of Multiphysics, 15(3), 291-309. https://doi.org/10.21152/1750-9548.15.3.291

• Journal Article Type: Article
• Acceptance Date: Mar 9, 2021
• Online Publication Date: Jul 11, 2021
• Publication Date: Jul 11, 2021
• Deposit Date: Jan 16, 2024
• Publicly Available Date: Jan 22, 2024
• Journal: The International Journal of Multiphysics
• Print ISSN: 1750-9548
• Publisher: International Society of Multiphysics
• Peer Reviewed: Peer Reviewed
• Volume: 15
• Issue: 3
• Pages: 291-309
• DOI: https://doi.org/10.21152/1750-9548.15.3.291
• Keywords: Fluid Flow and Transfer Processes; Mechanics of Materials; Modeling and Simulation; Numerical Analysis; Computational Mechanics