By A. S. Taylor, D. J. Eckford (Eds.)
Read or Download Aircraft Loading Action Problems (Proceedings of a Symposium held at Farnborough on 28th October, 1966) PDF
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Additional resources for Aircraft Loading Action Problems (Proceedings of a Symposium held at Farnborough on 28th October, 1966)
166 5 i 31 discussion about the uncertainties of the actual applied loadings, especially those coming from the pilot. He pointed cut that by applying such concepts as manoeuvre demand control one could limit the variety cf things a pilot could do. Mr. F'insker said that one area in which he had become involved in Loading Actions was that of inertia cross-coupling. There,a large amount of the trouble stemmed from allowing the pilot to use the controls in a way which was of no utility and very often it was possible to eliminate the problems altogether by putting stops on the control surfaces.
This pcssiblllty is being investigated at the moment. (3) to calculate the stringer stresses at the three tine IntervLlls whxh correspond to maximum wing bendlng moment, maximum fuel lnertla factor and maximum external air load. It is then assumed that aqy other time intervals will give loads only marginally wcrse (< 2%) than the worst value from the three times investigated. This method has generally been used in deriving the Trident gust loads and checks using method (2) have shown that in the vast majority of Cases It gives the correct design loads within a very small error.
When dealing with low-speed aircraft where Mach number effeots are negligible, there will be a unique value for the aircraft pitching moment coefficient and aerodynamic centre position associated with any aircraft configuration. On modern high-speed aircraft, however, there is the added complication that the overall CM and aerodynamic centre vary with Mach 0 number and so do the distributions of lift ani pitohing moment over the wings, talplane and fuselage. For the aircraft's complete range of operating Mach numbers, therefore, there is required a definition of the various aerodynamic load gradings ponding values of overall In practice, the order is ficients which are derived have to be calculated to .
Aircraft Loading Action Problems (Proceedings of a Symposium held at Farnborough on 28th October, 1966) by A. S. Taylor, D. J. Eckford (Eds.)