Abstract
This paper concerns with recent experiences made at CIRA on the subject of filament wound composite anisogrid structures. The main phases of design, manufacturing and testing are explored giving a rather comprehensive methodology to address this kind of concept toward primary structures for aerospace application aiming at structural efficiency and process reliability. Nomenclature R = shell radius L = shell height P = total compressive force in the axial direction M = shell mass H = shell thickness n c = number of hoop ribs n h = half total number of helical ribs ac = distance of hoop ribs a h = distance of helical ribs b c = width of hoop ribs b h = width of helical ribs ϕ = helical angle E = Young Modulus of helical ribs σ = compressive strength of helical ribs ρh = mass density of helical ribs ρc = mass density of hoop ribs h = height of pins
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