Fracture of an aircraft's landing gear

Azevedo, César Roberto de Farias; Hippert, Eduardo

doi:10.1016/s1350-6307(01)00020-6

Cited by 19 publications

(2 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Maximum deformation of the first two order modal located in the central part of knife axis tube can be 0.46nm. Adding support in intermediate place of knife shaft can effectively reduce the strain that improve the stiffness of the blade axis in later optimal design process [7] .…”

Section: Analysis Of Simulation Resultsmentioning

confidence: 99%

Based on NX NASTRAN Finite Element Analysis of Rotary Blade Axis

Wang²,

Zhang

2013

AMM

View full text Add to dashboard Cite

Rotary tillage is the most common method of modern farming land and the key component which transmits torque and bears soil counterforce and pound. Rotary blade axis（1GBF-12A）was studied in this paper using 3D design software(UG) and finite element analysis software(NX NASTRAN) to establish model analysis and static analysis. The result that the vulnerable area is at the middle of Blade Axis was obtained. The strongest bending stress and position of the Blade Axis is calculated. The research offers theoretical basis for improving future design.

show abstract

Section: Analysis Of Simulation Resultsmentioning

confidence: 99%

Based on NX NASTRAN Finite Element Analysis of Rotary Blade Axis

Wang²,

Zhang

2013

AMM

View full text Add to dashboard Cite

show abstract

“…Azevedo and E. Hippert Jr studied the failure cause of left main landing gear of an aircraft which encountered onepoint landing impact on a slope causing the fracture of its external cylinder. 18 Different techniques like visual inspection, metallographic investigation, mechanical tests including tensile, toughness, hardness test, etc. were performed.…”

Section: Introductionmentioning

confidence: 99%

Comprehensive design of an oleo-pneumatic nose landing gear strut

Ahmad

Shah

Shams

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

A comprehensive design cycle of a nose landing gear strut having an oleo-pneumatic shock absorber for a lightweight aircraft is proposed. Design and analysis of a retractable nose landing gear according to Airworthiness Standards FAA FAR Part 23 have been carried out. This research is focused on mathematical modeling of an oleo-pneumatic strut with an analytical solution of design variables at static and dynamic loading conditions. The variation of spring and damping characteristics of an oleo-pneumatic shock absorber with the stroke length is also presented. Feasibility of equivalent mechanical spring and damper along with comparison of pneumatic as air spring and oleo as hydraulic damper is studied. Numerical integration technique was used to solve the dynamic model of an oleo-pneumatic strut with forcing function of an impact force during touch down scenario. Energy conservation principle was used to determine height required for drop tests. Parametric study of anteversion angle within the constraints of ground clearance and volume in the fuselage determined an optimized angle of nose landing gear strut. Based on the maximum pressure and impact force encountered during landing, the hydraulic cylinder and piston design was finalized. In order to validate the proposed design cycle for preliminary phase, a structural integrity of cylinder and piston assembly was carried out using finite element analysis. Deformation, maximum stresses and factor of safety validated the proposed design cycle of a nose landing gear strut specific to a general aviation aircraft having all up mass of 1600 Kg.

show abstract

Suspension and landing gear failures

Ossa

Paniagua

2016

Handbook of Materials Failure Analysis With Case Studies From the Aerospace and Automotive Industries

View full text Add to dashboard Cite

Fracture of an aircraft's landing gear

Cited by 19 publications

References 19 publications

Based on NX NASTRAN Finite Element Analysis of Rotary Blade Axis

Based on NX NASTRAN Finite Element Analysis of Rotary Blade Axis

Comprehensive design of an oleo-pneumatic nose landing gear strut

Suspension and landing gear failures

Contact Info

Product

Resources

About