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Abstract

Shimmy vibration is a very important type of motion in the landing gear system during either the takeoff or landing of an aircraft. Energy input for this type of vibration is provided from the kinetic energy of the forward motion of the aircraft. As a result, this energy initiates a self-excited type of vibration in the wheels that may lead to instabilities. An attempt is made to develop a dynamical model for the aircraft nose gear to investigate its transient response for the lateral deviations and shimmy angles. Variations of different design parameters—namely, the energy absorption coefficient of the shimmy damper and the location of the gravity center of the landing gear—are studied. Results are presented graphically to facilitate the investigation of landing gear shimmy vibration.

Keywords

Aircraft landing gear self-excited system shimmy vibration stability analysis

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References

Black, J. , 1976, "Realistic evaluation of landing gear shimmy stabilization by test and analyses," SAE Paper No. 760496. Conway, H.J. , 1958, Landing Gear Design, Chapman & Hall, London. Currey, N.S. , 1982, Landing Gear Design Handbook, Lockheed Georgia Company , Marietta.

Grossman, T.D. , 1980, "F-15 landing gear shimmy, taxi and test and correlative analyses," SAE Paper No. 801239. Pacejka, H.B. , 1973, "Approximate dynamic shimmy response of pneumatic tires ," Vehicle System Dynamics 2, 49-60. Podgorski, W.A. and Krauter, A.I. , 1975, "The wheel shimmy problem: Its relationship to wheel and road irregularities," Vehicle System Dynamics 4, 9-41.

Van der Valk, R. and Pacejka, H.B. , 1993, "An analyses of a civil aircraft main landing gear shimmy failure," Vehicle System Dynamics 22, 97-121.

Shimmy Vibration Analysis of Aircraft Landing Gears

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