Abstract

Minimum-weight equations for failure of solid and wide columns, plates and plate assemblies (crippling), and optimum stringer panels are presented in terms of suitable structural loading and material-efficiency parameters. From these equations the comparative structural efficiency of plates and stringer panels was investigated. Similarly, the comparative efficiency of various materials was studied for elevated-temperature, stringer-panel applications. By analytically determining the optimum spacing of ribs or webs in stringer panel-rib or multiweb construction, respectively, a composite structure of minimum weight is obtained. For such structures the structural-loading and material-efficiency parameters are generally different from those obtained for the individual elements. Typical results are presented for composite structures and some general considerations are presented for selection of materials for thermal-flight aircraft.

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