Deflection Model of a CT4-A Undercarriage.
AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)
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In this Australian report, a relationship between applied loads and corresponding bending moment for a CT4-A undercarriage is determined to enable appropriate fatigue test loads to be evaluated. A mathematical model is derived to determine the significant deflection parameters of a loaded CT4-A undercarriage, which is represented as an eccentrically loaded tapered beam mounted at a torsional restraint. A general computer program was written to implement the analysis. Results for the undercarriage were then obtained for a range of loading cases. An empirical equation relating fatigue test loads to bending moment for the undercarriage was fitted. Originator-supplied keywords includes BeamsStructural Deflection Aircraft structures and LoadsForces.
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