IJERT-EMS
IJERT-EMS

Landing Gear of an Aircraft Structure: A Review


Landing Gear of an Aircraft Structure: A Review
Authors : Anurag Dubey, Shashwat Gupta , Vamsi Krishna Undavalli, Balakrishna Bodramoni
Publication Date: 02-12-2015

Authors

Author(s):  Anurag Dubey, Shashwat Gupta , Vamsi Krishna Undavalli, Balakrishna Bodramoni

Published in:   International Journal of Engineering Research & Technology

License:  This work is licensed under a Creative Commons Attribution 4.0 International License.

Website: www.ijert.org

Volume/Issue:   Volume. 4 - Issue. 12 , December - 2015

e-ISSN:   2278-0181

 DOI:  http://dx.doi.org/10.17577/IJERTV4IS120005

Abstract

The landing gear system of an aircraft is a system. It also absorbs the energy from the impact of landing Numerical type simulation has become highly invaluable tool for the assessment of the landing gear type dynamics also as well as of aircraft landing structure gear interaction. This paper also describes the normal structure review of a simple landing-gear structure model system, and which is accurately simulates with the energy system absorbed by the gear without the adding substantial structure and complexity with the model. it carries the structure aircraft weight at all require ground operations, including, landing, take off, taxiing, and towing. In future we know that advances in computational type speed have made aircraft and high spacecraft crash simulations design using an explicit, transient type dynamic, finite element analysis (FEM) code are the more feasible. For a plane crash model type system the landing gear is also exact response is approximated work with a many strong spring where many different force applied to the different fuselage. And it is also computed in a user-written works type. Helicopter crash type simulations which is using this approach that are compared with different necessary data is also acquired with the experimental method and data from a full structure crash structure test can be achieved by with the use of an aircraft of a composite. Depends on type of landing gear systems is also presented. Specifically, a nonlinear type model can easily developed which is simulated, and against static and dynamic data test data. Many type model includes nonlinear structure effects such as a velocity type squared related high damping, poly tropic gas law, stick-slip friction, a geometry governed with the high model structure for the high discharge type coefficients and methods, effects a nonlinear spring and damping model structure.

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