NDLI: Preliminary weight and costs of sandwich panels to distribute concentrated loads

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Preliminary weight and costs of sandwich panels to distribute concentrated loads

Content Provider	NASA Technical Reports Server (NTRS)
Author	Belleman, G. McCarty, J. E.
Copyright Year	1976
Description	Minimum mass honeycomb sandwich panels were sized for transmitting a concentrated load to a uniform reaction through various distances. The form skin gages were fully stressed with a finite element computer code. The panel general stability was evaluated with a buckling computer code labeled STAGS-B. Two skin materials were considered; aluminum and graphite-epoxy. The core was constant thickness aluminum honeycomb. Various panel sizes and load levels were considered. The computer generated data were generalized to allow preliminary least mass panel designs for a wide range of panel sizes and load intensities. An assessment of panel fabrication cost was also conducted. Various comparisons between panel mass, panel size, panel loading, and panel cost are presented in both tabular and graphical form.
File Size	9142477
Page Count	104
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19760011444
Archival Resource Key	ark:/13960/t0fv3bt2f
Language	English
Publisher Date	1976-02-15
Access Restriction	Open
Subject Keyword	Structural Mechanics Panels Weight Mass Stress Analysis Cost Effectiveness Aluminum Epoxy Compounds Graphite Sandwich Structures Load Distribution Forces Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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