Panels with integral stiffeners made with woven fabric in two-dimensional, cross-ply layups. Local skin buckling does not cause collapse of panels, and ultimate failure occurs at loads 10 to 20 percent above buckling loads. For panels subjected to in-plane loading, separation of stiffeners from panel skins was not problem. High-temperature structural applications on advanced aircraft and spacecraft include leading edges, fairings, and control surfaces.
Stiffened Carbon/Carbon Compression Panels
NASA Tech Briefs ; 16 , 4
01.04.1992
Sonstige
Keine Angabe
Englisch
Optimization of stiffened panels under compression
Tema Archiv | 1986
|Outstand failure in stiffened steel compression panels
TIBKAT | 1975
|Stiffened steel compression panels : a design approach
TIBKAT | 1974
|An approach to stiffened steel compression panels
TIBKAT | 1973
|Stress distribution in stiffened panels under compression
Engineering Index Backfile | 1937
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