By Jan Roskam
A useful encyclopedia of ancient airplane information, layout equations and strategies.
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Additional resources for Airplane Design Parts I-VII
The interior structure to which the skin or plating is attached consists of longerons, frames, bulkheads, stringers, gussets, and possibly intercostal members riveted, bolted, or bonded together to form a rigid structure that shapes the fuselage. The skin or plating is riveted or bonded to the structure to form the complete unit. The types and thicknesses of materials used for covering the fuselage of a typical light airplane are shown in the drawings of Fig. 2-20. The thickness of the skin varies according to position on the fuselage.
This type of design is found on many corporate and transport aircraft and is illustrated in Fig. 2-25. Because of their size, transport aircraft fuselages are commonly constructed by first building subassemblies of long panels several feet high, as shown in Fig. 2-26. These panels are then joined on a mating jig to form the circular shape of a fuselage section, as shown in Fig. 2-27. The fuselage is then assembled by connecting the forward, mid, and aft fuselage sections. The forward section tapers the cross section of the fuselage to the front of the aircraft.
When the purpose of a particular design is established, the designers provide structure according to strict standards established by the Federal Aviation Administration to ensure safety. 5 times the maximum expected forces. To be certified by the Federal Aviation Administration, the structural strength (load factor) on airplanes must conform with the standards set forth by Federal Aviation Regulations. The loads imposed on the wings in flight are stated in terms of load factor. , the actual load supported by the wings divided by the total weight of the airplane.
Airplane Design Parts I-VII by Jan Roskam