A Study on Fatigue Fracture Failure of UAV Landing Gear

Vignesh, Arun; Vivek, Anupam

doi:10.26634/jme.6.1.3736

Cited by 2 publications

(1 citation statement)

References 2 publications

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“…By using ANSYS Parametric Design Language (APDL) to analyze usable structures, we discovered fatigue fractures in UAV landing gear, contour effectiveness, and the stress and fracture growth rates associated with fatigue fractures. By performing static analyses, we located critical regions [9]. …”

Section: Introductionmentioning

confidence: 99%

A study on static structural of non-rotor unmanned aerial vehicle

et al. 2017

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Abstract. Multi-rotor unmanned aerial vehicles (UAVs) have become common in recent years, but non-rotor UAVs are still relatively rare. This study used an aerodynamic model to replace the multi-rotor design concept and examine load bearing capabilities, specifically for delivery of medical goods by non-rotor UAV. We use static structural simulations for static analysis and fatigue analysis to investigate the capabilities of different structural materials. The simulation results combined fatigue strength verifications, structural safety factor calculations, and finite element analyses to calculate parameters like total deformation, stress ratios, and strain magnitudes to analyze structural fatigue life. The analyses indicated that the factors of safety and fatigue lifetimes of two structural materials far exceeded standard values. They can be used to optimize designs that prevent plastic deformation and breakage. Time and money are saved in the research and development process by carrying out these calculations and static analyses of physical properties before prototypes are actually built.

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Section: Introductionmentioning

confidence: 99%

A study on static structural of non-rotor unmanned aerial vehicle

et al. 2017

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Simulation, Fabrication and Testing of UAV Composite Landing Gear

et al. 2022

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This study concerns the use of the fused filament fabrication technique to create models of the landing gear of an unmanned aircraft. These components are made of filament with short fibers (chopped fibers) of carbon fiber and fiberglass. In order to identify the material with the high mechanical strength, the designed models were subjected to a finite element analysis and to a three-point bending test, followed by a microscopic examination of the tested components. Following a comparative study, both the finite element analysis results and the three-point bending test results provided similar results, with a relative error of 2%, which is acceptable in the aviation field. After analyzing all the results, it was found that the carbon fiber-reinforced polymer material has the highest mechanical performance, with a bending strength of 1455 MPa. Among the fused filament fabricated landing gears, the one with the best mechanical performance was polyethylene terephthalate with short carbon fiber, which had a bending strength of 118 MPa. Microscopic analysis of the landing gear models, manufactured by the fused filament fabrication process, indicated the typical defects of composite filaments: voids and interlayer voids.

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A Study on Fatigue Fracture Failure of UAV Landing Gear

Cited by 2 publications

References 2 publications

A study on static structural of non-rotor unmanned aerial vehicle

A study on static structural of non-rotor unmanned aerial vehicle

Simulation, Fabrication and Testing of UAV Composite Landing Gear

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