Effects of Spring and Damper Elements in Aircraft Landing Gear Dynamics
Ali Dinc1, Yousef Gharbia2
1Ali Dinc*, Department of Engineering and Technology, American University of the Middle East, Kuwait.
2Yousef Gharbia, Department of Engineering and Technology, American University of the Middle East Kuwait.

Manuscript received on January 05, 2020. | Revised Manuscript received on January 25, 2020. | Manuscript published on January 30, 2020. | PP: 4265-4269 | Volume-8 Issue-5, January 2020. | Retrieval Number: D9247118419/2020©BEIESP | DOI: 10.35940/ijrte.D9247.018520

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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)

Abstract: In this study a typical Aircraft Landing Gear with shock absorber was modeled a Mass-Spring-Damper System. Basic components of the system were explained. The equations of the model was presented. Aircraft Landing Gear was also modeled in Matlab/Simulink for a given set of aircraft parameters. A case study for an Aircraft Landing Gear was solved and results were presented. Results included the variation of spring (k1 and k2) and damping coefficient (b) in a given interval to show their effects on the impact force and displacement of landing gear as main outputs to consider. Effect of damping coefficient (b) on impact force was found to be highest (3.76%), spring coefficient (k1) effect is moderate (2.29%), and spring coefficient (k2) is lower (0.97%), for a change of ±10% of coefficients.
Keywords: Aircraft Landing Gear, Mass-Spring-Damper System, Shock Absorber, System Modeling.
Scope of the Article: Evolutionary Computing and Intelligent Systems.