A Method of calculating the compressive strength of Z-stiffened panels that develop local instability

A method, based on the elastic theory for plate buckling and test results for 24S-T aluminum-alloy Z-stiffened panels, is shown for calculating the compressive strength of Z-stiffened panels that develop local instability. This method can be used to calculate the critical compressive stress above, a...

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Bibliographic Details
Main Author: Gallaher, George L., (Author)
Corporate Author: United States. National Advisory Committee for Aeronautics.
Other Authors: Boughan, Rolla B.
Format: eBook
Language: English
Published: Washington, D.C. : National Advisory Committee for Aeronautics, 1947.
Series: Technical note (United States. National Advisory Committee for Aeronautics) ; no. 1482.
Subjects:
Plates (Engineering)
Strains and stresses.
Buckling (Mechanics)
Mathematical analysis.
elektronické knihy
electronic books
ISBN: 9781680156102
1680156101
Physical Description: 1 online resource (15 pages) : illustrations, tables

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Table of contents

LEADER 02693cam a2200445 i 4500
001 kn-ocn919093676
003 OCoLC
005 20240717213016.0
006 m o d
007 cr cn|||||||||
008 150824s1947 dcuad obt f000 0 eng d
040 |a KNOVL  |b eng  |e rda  |e pn  |c KNOVL  |d ZCU  |d UAB  |d DKU  |d OCLCQ  |d CEF  |d RRP  |d YOU  |d S2H  |d OCLCO  |d COP  |d OCLCO  |d OCLCQ  |d UPM  |d OCLCQ  |d OCLCO  |d OCLCL  |d SXB 
020 |a 9781680156102  |q (electronic bk.) 
020 |a 1680156101  |q (electronic bk.) 
035 |a (OCoLC)919093676 
100 1 |a Gallaher, George L.,  |e author. 
245 1 2 |a A Method of calculating the compressive strength of Z-stiffened panels that develop local instability /  |c by George L. Gallaher and Rolla B. Boughan. 
264 1 |a Washington, D.C. :  |b National Advisory Committee for Aeronautics,  |c 1947. 
300 |a 1 online resource (15 pages) :  |b illustrations, tables 
336 |a text  |b txt  |2 rdacontent 
337 |a computer  |b c  |2 rdamedia 
338 |a online resource  |b cr  |2 rdacarrier 
490 1 |a National Advisory Committee for Aeronautics technical note ;  |v number 1482 
500 |a "November 1947." 
500 |a NACA TN No. 1482. 
504 |a Includes bibliographical references. 
506 |a Plný text je dostupný pouze z IP adres počítačů Univerzity Tomáše Bati ve Zlíně nebo vzdáleným přístupem pro zaměstnance a studenty 
520 3 |a A method, based on the elastic theory for plate buckling and test results for 24S-T aluminum-alloy Z-stiffened panels, is shown for calculating the compressive strength of Z-stiffened panels that develop local instability. This method can be used to calculate the critical compressive stress above, as well as within, the elastic range. For stresses above three-fourths the compressive yield stress the method can be used for the approximate determination of the average compressive stress at maximum load. 
590 |a Knovel  |b Knovel (All titles) 
650 0 |a Plates (Engineering) 
650 0 |a Strains and stresses. 
650 0 |a Buckling (Mechanics) 
650 0 |a Mathematical analysis. 
655 7 |a elektronické knihy  |7 fd186907  |2 czenas 
655 9 |a electronic books  |2 eczenas 
700 1 |a Boughan, Rolla B. 
710 1 |a United States.  |b National Advisory Committee for Aeronautics. 
776 0 8 |i Print version:  |a Gallaher, George L.  |t Method of calculating the compressive strength of Z-stiffened panels that develop local instability  |w (OCoLC)656605606 
830 0 |a Technical note (United States. National Advisory Committee for Aeronautics) ;  |v no. 1482. 
856 4 0 |u https://proxy.k.utb.cz/login?url=https://app.knovel.com/hotlink/toc/id:kpMCCSZSPU/method-of-calculating?kpromoter=marc  |y Full text 

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