THE case to be investigated is shown diagrammatically in fig. 8 (a). In practice, it represents the top or bottom panels of a two‐spar skin‐covered wing, where the front and rear spars have different flange areas. Using the notation of FIG. 8, we take for our basic solution the expression w=(P sinh λks + Q cosh λks)cos λz…F(1) A rigid‐body rotation may be imposed on this, if desired, to make the displacement at the point s=a, z=0 the same as at the origin, but as this will not affect the stresses it need not be included in equation F(l). It has, however, been found necessary to include such a rotation if it is required to find the final expression for the displacement w, in order to make the integral (which represents w) convergent. The present investigation has, however, only been carried as far as the determination of the end loads in each flange, since this information will in practice be sufficient for the design of the panel, as regards riveting of flanges to skin, and the skin reinforcing required.
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