Failure analysis of a broken support strut of an aircraft landing gear

Hameed, Asad; Zubair, Ossama; Shams, Taimur Ali; Javed, Ali; Mehmood, Zahid

doi:10.1016/j.engfailanal.2020.104847

Cited by 19 publications

(6 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The shock absorber, which is schematically illustrated in Figure 2, is powered by a combination of pneumatic, hydraulic, and frictional forces. As the cylinder's volume decreases and internal pressure increases, there are forces operating on the seal and its contact surface that are frictional, hydraulic, and pneumatic (Hameed et al, 2020).…”

Section: Shock Absorbers/ Oleo Strutmentioning

confidence: 99%

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

View full text Add to dashboard Cite

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.

show abstract

Section: Shock Absorbers/ Oleo Strutmentioning

confidence: 99%

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

View full text Add to dashboard Cite

show abstract

“…In particular, aeronautic electromagnetic brakes are key components of the landing gear of aircraft, which is considered one of the most critical systems for flight safety [2], as almost 60% of failures occur during landing and take-off operations [3].…”

Section: Introductionmentioning

confidence: 99%

Experimental Wear Characterization and Durability Enhancement of an Aeronautic Braking System

Logozzo

Valigi

2023

Applied Sciences

View full text Add to dashboard Cite

This paper is focused on the experimental wear characterization of an electromagnetic braking system used for helicopters. The characterization was performed through the evaluation of some monitoring parameters during endurance tests on a test bench and through the visual analysis of the worn surfaces after the tests. The monitoring parameters were the engagement threshold voltage, the release threshold voltage, the inductance, and the braking torque, which are directly correlated with the wear progress. The visual analysis allowed the assessment of the wear extent and the distribution of wear particles at the interfaces. The test performed on the initial base configuration, having ten springs and carbon fibers as friction materials, demonstrated that the braking system had insufficient durability in terms of actuation cycles. The results allowed the design of two new configurations based on different brake architectures and on different friction pairs. One of the new configurations was based on a reduction in the number of springs (eight-spring configuration), and the second one was based on the employment of a different friction material (NAO configuration). Both of these optimized configurations showed enhanced durability and wear resistance, but only the second one showed sufficient durability with respect to the requirements and was defined as acceptable. The final results showed a durability of 3000 actuation cycles for the base configuration, 4385 for the eight-spring configuration, and 35,223 for the NAO configuration. Nevertheless, the analysis of results allowed the cause of the wear phenomena to be studied and eventual further improvements in the system to be suggested.

show abstract

“…[ 1–3 ] However, due to complex alternating loads and strong impacts from the ground in service, the landing gear often suffers from microcracks, microfractures, unpredictable fatigue failures, and even surface fractures. [ 4,5 ] These unfavorable phenomena pose high risks to the overall safety of the aircraft. A few studies demonstrate that the surface strengthening technology can effectively improve the properties of 300M steel against fatigue fracture, enhance the reliability and safety of the component, and prolong the service life.…”

Section: Introductionmentioning

confidence: 99%

Microstructure Evolution and Properties of Gradient Nanostructures Subjected to Laser Shock Processing in 300M Ultrahigh‐Strength Steel

Xiong

Chen

et al. 2021

steel research int.

View full text Add to dashboard Cite

Herein, gradient nanostructures (GNs) are created in 300M ultrahigh‐strength (UHS) steel by laser shock processing (LSP). Microstructure evolution and properties of GNs subjected to LSP with different pulse energies are thoroughly characterized on 3D profiler, scanning electron microscope (SEM), transmission electron microscope (TEM), X‐ray diffractometer (XRD), X‐ray stress analyzer, nanoindenter, and tensile tester. Results show successful creations of GNs in 300M steel after LSP treatments. With the increase in pulse energy, the size of the surface layer is refined from 15 nm (3 J) to 10 nm (7 J), and the corresponding grains are amorphized to some extent. Meanwhile, many substructure defects such as dislocation tangles and deformation twins (DTs) are noted in the subsurface. The dislocation density and the number of DTs increase with the pulse energy. Further, the high compressive residual stress is introduced to the 300M steel surface after LSP, and the corresponding hardness is improved substantially. The compressive residual stress, depth of the affected layer, and the hardness rise significantly with the pulse energy. Apart from improvements in strength and plasticity, the fracture morphology is changed from a typical ductile fracture to quasicleavage and ductile mixed fracture.

show abstract

Failure analysis of a broken support strut of an aircraft landing gear

Cited by 19 publications

References 16 publications

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

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

Experimental Wear Characterization and Durability Enhancement of an Aeronautic Braking System

Microstructure Evolution and Properties of Gradient Nanostructures Subjected to Laser Shock Processing in 300M Ultrahigh‐Strength Steel

Contact Info

Product

Resources

About