Analysis of Different Designed Landing Gears for a Light Aircraft

The design of a landing gear is one of the fundamental aspects of aircraft design. The need for a light weight, high strength, and stiffness characteristics coupled with techno economic feasibility are a key to the acceptability of any landing gear construction. In this paper, an approach for analyzing two different designed landing gears for an unmanned aircraft vehicle (UAV) using advanced CAE techniques will be applied. Different landing conditions have been considered for both models. The maximum principle stresses for each model along with the factor of safety are calculated for every loading condition. A conclusion is drawing about better geometry.

• Essam A. Al-Bahkali

• Landing Gear
• Model
• Finite Element Analysis
• Aircraft.

[1] D.W. Young, “Aircraft Landing Gears–Past Present and Future”, Proceeding of IME, Vol. 200, No. D2, pp 75-92, 1986.
[2] M. H. Sadraey, “Aircraft Design: A Systems Engineering Approach”,
Wiley, 2012.
[3] A. Goyal, “Light Aircraft Main Landing Gear Design and
Development”, International ANSYS Conference Proceedings, 2000.
[4] R.H. Mallett and P.V. Marcal, “Finite Element Analysis of Non
structures”, First Division, Vol. 94, No. ST9, pp. 2081 – 2105, 1968.
[5] Metals Handbook, Properties and Selection: Nonferrous Alloys and Special-Purpose Materials, ASM International, Vol.2, 10th edition. 1990.
[6] ABAQUS, User’s Manual, Version 6.9, 2010.