In an aircraft fuselage or motor gondola wherein all the stresses occurring are taken up by a spatial skeleton structure a, an outer covering is provided formed by individual reinforced panels b, c, d, e, each covered on one side with fabric, sheet‐metal or plywood f, g, h, i. All the panels may be removably secured to the structure a by means of clamps, screws, bolts, or the like, or some only of the panels at places where easy access to the interior of the fuselage is desired, the remainder of the fuselage being provided with a non‐removable covering. Each panel is reinforced by a lattice structure, or by profiled members, or by other means and may be mounted with its covered surface towards the interior of the fuselage. The panels may be interchangeable and some may be covered on both sides.
(1934), "Month in the Patent Office: A Selection of the More Important Aircraft and Engine Specifications Published Recently", Aircraft Engineering and Aerospace Technology, Vol. 6 No. 8, pp. 230-230. https://doi.org/10.1108/eb029839
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