FE Analysis for Landing Gear of Test Air Craft

Imran, Mohammed; Ahmed, Ramiz; Haneef, Mohamed

doi:10.1016/j.matpr.2015.07.228

Cited by 16 publications

(8 citation statements)

References 5 publications

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“…Following study was conducted in order to evaluate the properties of equivalent mechanical spring. For that purpose, the air spring force of oleo pneumatic as mentioned in equation ( 5) was equated with mechanical spring force and value of mechanical spring constant k was obtained as shown in equation (7).…”

Section: Equivalent Mechanical Springmentioning

confidence: 99%

“…In compliance with drop test, either complete aircraft or a landing gear unit must be used for the drop test. The drop height must not be less than the height calculated by equation (12). However, It is important to mention that Airworthiness standard FAA FAR part 23, clause 23.725 limits the drop height between (9.2 in �18.7 in) which came out to be 350 mm (13.78 in) for the designed oleo pneumatic nose landing gear of the aircraft in this A similar relation was developed by equating kinetic and potential energy of the system.…”

Section: Drop Testmentioning

confidence: 99%

“…Imran, Shabbir and Haneef studied dynamic response of landing gear. 7 In this work, CAD model of the designed landing gear was made and Rigid Body Element (RBE) were defined for load transfer. Coupling constraints were also defined and static along with dynamic loads and modal frequencies were calculated using ANSYS V R .…”

Section: Introductionmentioning

confidence: 99%

“…Mohammed Imran designed a landing gear with the help of CAD software and static loads were analyzed under various constraints using ANSYS V R to validate structural safety. 12 The number of loads used were specified by FARC rulebook for level and one-wheel landing. Yuan Li et al proposed the use of inerter with shock absorbers to enhance energy dissipation performance of landing gear.…”

Section: Introductionmentioning

confidence: 99%

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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:

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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.

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Section: Equivalent Mechanical Springmentioning

confidence: 99%

Section: Drop Testmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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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:

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“…The investigation focused on an accident in which the nose of the landing gear fork of a light aircraft failed during landing. Mohammed et al [12], in their work, focused on the structural components, made of composite materials, of a landing gear. Structural safety for static and spectrum loads is analysed using ANSYS.…”

Section: Introductionmentioning

confidence: 99%

Investigation on the static and dynamic structural behaviors of a regional aircraft main landing gear by a new numerical methodology

Caputo

Luca

Greco

et al. 2017

Frattura Ed Integrità Strutturale

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In this paper, a new methodology supporting the design of landing gears is proposed. Generally, a preliminary step is performed with simplified FE model, usually one-dimensional, to achieve the reaction forces involving each component during all aforementioned aircraft operations. Though this approach gives a valid support to the designer, it is characterized by several problems, such as the related approximations. So, it is important, by a numerical point of view, to develop an isostatic FE model equivalent to the real one. In fact, if the landing gear is modelled as hyperstatic, the static equilibrium equations are insufficient for determining the internal forces and reactions on each sub-component; so, the modelled material properties and geometries assume an increasing importance, which gets the model too approximating. The proposed methodology consists of achieving the reaction forces by means of multibody simulations, by overcoming such problems, since each component is modelled as rigid. In this paper, also a FE model for the investigation of the structural response is proposed. Aimed to Certification by Analysis purposes, the developed multibody and the FE models have been assessed against an experimental landing gear drop test carried out by Magnaghi Aeronautica S.p.A., according to the EASA CS 25 regulations. Investigation on the static and dynamic structural behaviors of a regional aircraft main landing gear by a new numerical methodology, Frattura ed Integrità Strutturale, 43 (2018) 191-204.

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