Landing Gear Leg Fatigue Life Analysis for Light Aircraft

Gerhardinger, David; Abramović, Borna; Fratrović, Tomislav; Domitrović, Anita

doi:10.1016/j.trpro.2022.09.003

Cited by 3 publications

(2 citation statements)

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“…However, most of the parts are not engaged in stress distribution, thus the nose gear of a small passenger aircraft is simplified to serve as a model for the stress analysis, which only considers the parts and designs that are involved in stress distribution. An aircraft's fixed landing gear is made up of the following primary parts such as Tires, Wheels, Brakes, Axles (Gerhardinger et al, 2022;Sonowal et al, 2021).…”

Section: Nomenclature Of Landing Gearmentioning

confidence: 99%

“…Firstly, there is lack of studies on small passenger aircraft nose landing gear considering runway gradient using computational analysis utilizing ANSYS to evaluate stress distribution. Considering the Nepalese airports and their unique challenges such as Nepal's topography, short-runways, STOL aircraft usage, and operational considerations (Bk, 2017;Gerhardinger et al, 2022;Voskaki et al, 2023).…”

Section: Research/knowledge Gapmentioning

confidence: 99%

See 1 more Smart Citation

Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Yadav,

Sudhakar

2023

Orchid Acad. Siraha

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Landing gear failures are a major cause of aircraft failures because they are an integral part of the aircraft's development. According to the Federal Aviation Administration (FAA), 50% of all aircraft failures occur during take-offs and landing. The landing gear of a short take-offs and landing (STOL) aircraft has had its static and dynamic forces analyzed analytically and numerically. SOLIWORKS is used to model the landing gear, and ANSYS is used to perform the numerical simulation results. Following it, the model is examined for stress and deformation with the boundary conditions and computed loads into account. This study uses structural finite element analysis (FEA) to analyze the nose gear's stress behavior and displacement during landing, as well as to assess the effect of the runway gradient. Utilizing a comprehensive numerical simulation, the landing gear of a real material Twin-Otter STOL aircraft has been demonstrated to be subjected to a dynamic force of 3653.26N, a pneumatic pressure of 1.59MPa, a bead pressure of 7.97MPa, and a vertical force of 1672.31lbs on level runways, or runways with no gradient. These findings will increase the level of confidence of aircraft manufacturers to make necessary appropriate design of STOL aircraft’s landing gear. It may can decrease the aircraft accidents and increase human life safety ultimately saving valuable time and resources too.

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Section: Nomenclature Of Landing Gearmentioning

confidence: 99%

Section: Research/knowledge Gapmentioning

confidence: 99%