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2 Journal of KONES

2 2006

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Dynamic study of aircraft gear behaviour in some unusual conditions

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Niezgoda T. , Małachowski J. , Budzyński A.

tom Vol. 13, No. 3

245-254

The paper presents CAE MBS analysis of aircraft front landing gear behaviour in unusual situations that can be caused by unpredictable obstacles. Numerical tools were applied, because real investigations can be relatively expensive and dangerous. One of unusual maintenance condition assumed increasing of the aircraft vertical velocity, caused by a loss of uplift forces (result of decreasing the horizontal velocity to shorten the airfield length needed to dissipate aircraft energy). The other analyzed maintenance condition assumed the aircraft landing with horizontal velocity, increased of a large percentage in comparison with its maximum value allowed by the aircraft manufacturer. Simulation also provided the gear dynamics analysis while crossing over obstacles placed on slightly damaged or makeshift airfield. During CAE tests, Lagrange spring/dumper elements used to simulate the behavior of deformable tyre and shock absorber oil-gas mixture. Simulations proved that increasing the vertical velocity of 25% and the horizontal one of 15% is safe for the aircraft and it can operate on damaged airfields. Investigations proved that aircraft maintenance conditions might be safely expanded, in comparison with its manufacturer suggestions. It enables the manufacturer to look for new and aircraft-safe applications that require special landing capabilities: Special Team Transport or Medical Evacuation.

Numerical analysis of a front support landing gear dynamics as the example of chosen MCAD and CAE systems integration in the case of the military transport aircraft design

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Niezgoda T. , Małachowski J. , Budzyński A.

tom Vol. 13, No. 2

341-350

The paper presents the example of MCAD and CAE environments integration in the case of the military transport aircraft front gear dynamic analysis. The gear exact MCAD model is presented with the manner of its simplification. Simplified model is physically similar to the exact one: results of numerical static analysis are the same in both cases. To ensure the credibility of the dynamic analysis, a model kinematics one took place - the gear configuration changed (“airborne” - “airfield”) with the measurements of chosen values. Simulation was verified with the real experiment results. The gear drop test has been simulated with the measurement of the fall-down velocity and absorber displacement. By the progressive results comparison of digital and real experiments, the stiffness-dumping values were attached to the spring/dumper Lagrange elements that simulate the behavior of the absorber gas-oil mixture. The gear model shock sensitivity has been analysed by simulations of landing process with gear invasion through chosen airfield obstructions. Aircraft fall-down velocity can be safely increased by 30% and it can operate on slightly damaged concrete airfields and rough surfaces. The shimmy vibration model sensitivity took place. It is proved that such a phenomenon can’t appear during the correct aircraft maintenance.