Strength and stiffness of sandwich beams in bending
Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of san...
Ausführliche Beschreibung
Autor*in: |
Lingaiah, K. [verfasserIn] |
---|
Format: |
Artikel |
---|---|
Sprache: |
Englisch |
Erschienen: |
1991 |
---|
Schlagwörter: |
---|
Anmerkung: |
© Society for Experimental Mechanics, Inc. 1991 |
---|
Übergeordnetes Werk: |
Enthalten in: Experimental mechanics - Kluwer Academic Publishers, 1961, 31(1991), 1 vom: März, Seite 1-7 |
---|---|
Übergeordnetes Werk: |
volume:31 ; year:1991 ; number:1 ; month:03 ; pages:1-7 |
Links: |
---|
DOI / URN: |
10.1007/BF02325715 |
---|
Katalog-ID: |
OLC2058164520 |
---|
LEADER | 01000caa a22002652 4500 | ||
---|---|---|---|
001 | OLC2058164520 | ||
003 | DE-627 | ||
005 | 20230504082646.0 | ||
007 | tu | ||
008 | 200819s1991 xx ||||| 00| ||eng c | ||
024 | 7 | |a 10.1007/BF02325715 |2 doi | |
035 | |a (DE-627)OLC2058164520 | ||
035 | |a (DE-He213)BF02325715-p | ||
040 | |a DE-627 |b ger |c DE-627 |e rakwb | ||
041 | |a eng | ||
082 | 0 | 4 | |a 690 |q VZ |
100 | 1 | |a Lingaiah, K. |e verfasserin |4 aut | |
245 | 1 | 0 | |a Strength and stiffness of sandwich beams in bending |
264 | 1 | |c 1991 | |
336 | |a Text |b txt |2 rdacontent | ||
337 | |a ohne Hilfsmittel zu benutzen |b n |2 rdamedia | ||
338 | |a Band |b nc |2 rdacarrier | ||
500 | |a © Society for Experimental Mechanics, Inc. 1991 | ||
520 | |a Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. | ||
650 | 4 | |a Failure Load | |
650 | 4 | |a Sandwich Structure | |
650 | 4 | |a Shear Stiffness | |
650 | 4 | |a Sandwich Beam | |
650 | 4 | |a Flexural Stiffness | |
700 | 1 | |a Suryanarayana, B. G. |4 aut | |
773 | 0 | 8 | |i Enthalten in |t Experimental mechanics |d Kluwer Academic Publishers, 1961 |g 31(1991), 1 vom: März, Seite 1-7 |w (DE-627)129593990 |w (DE-600)240480-1 |w (DE-576)015086852 |x 0014-4851 |7 nnns |
773 | 1 | 8 | |g volume:31 |g year:1991 |g number:1 |g month:03 |g pages:1-7 |
856 | 4 | 1 | |u https://doi.org/10.1007/BF02325715 |z lizenzpflichtig |3 Volltext |
912 | |a GBV_USEFLAG_A | ||
912 | |a SYSFLAG_A | ||
912 | |a GBV_OLC | ||
912 | |a SSG-OLC-UMW | ||
912 | |a SSG-OLC-ARC | ||
912 | |a SSG-OLC-TEC | ||
912 | |a SSG-OLC-PHY | ||
912 | |a GBV_ILN_11 | ||
912 | |a GBV_ILN_20 | ||
912 | |a GBV_ILN_22 | ||
912 | |a GBV_ILN_23 | ||
912 | |a GBV_ILN_70 | ||
912 | |a GBV_ILN_2004 | ||
912 | |a GBV_ILN_2014 | ||
912 | |a GBV_ILN_2015 | ||
912 | |a GBV_ILN_2020 | ||
912 | |a GBV_ILN_4046 | ||
912 | |a GBV_ILN_4307 | ||
912 | |a GBV_ILN_4319 | ||
912 | |a GBV_ILN_4700 | ||
951 | |a AR | ||
952 | |d 31 |j 1991 |e 1 |c 03 |h 1-7 |
author_variant |
k l kl b g s bg bgs |
---|---|
matchkey_str |
article:00144851:1991----::teghnsifesfadihe |
hierarchy_sort_str |
1991 |
publishDate |
1991 |
allfields |
10.1007/BF02325715 doi (DE-627)OLC2058164520 (DE-He213)BF02325715-p DE-627 ger DE-627 rakwb eng 690 VZ Lingaiah, K. verfasserin aut Strength and stiffness of sandwich beams in bending 1991 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Society for Experimental Mechanics, Inc. 1991 Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. Failure Load Sandwich Structure Shear Stiffness Sandwich Beam Flexural Stiffness Suryanarayana, B. G. aut Enthalten in Experimental mechanics Kluwer Academic Publishers, 1961 31(1991), 1 vom: März, Seite 1-7 (DE-627)129593990 (DE-600)240480-1 (DE-576)015086852 0014-4851 nnns volume:31 year:1991 number:1 month:03 pages:1-7 https://doi.org/10.1007/BF02325715 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-UMW SSG-OLC-ARC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_70 GBV_ILN_2004 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_4046 GBV_ILN_4307 GBV_ILN_4319 GBV_ILN_4700 AR 31 1991 1 03 1-7 |
spelling |
10.1007/BF02325715 doi (DE-627)OLC2058164520 (DE-He213)BF02325715-p DE-627 ger DE-627 rakwb eng 690 VZ Lingaiah, K. verfasserin aut Strength and stiffness of sandwich beams in bending 1991 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Society for Experimental Mechanics, Inc. 1991 Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. Failure Load Sandwich Structure Shear Stiffness Sandwich Beam Flexural Stiffness Suryanarayana, B. G. aut Enthalten in Experimental mechanics Kluwer Academic Publishers, 1961 31(1991), 1 vom: März, Seite 1-7 (DE-627)129593990 (DE-600)240480-1 (DE-576)015086852 0014-4851 nnns volume:31 year:1991 number:1 month:03 pages:1-7 https://doi.org/10.1007/BF02325715 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-UMW SSG-OLC-ARC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_70 GBV_ILN_2004 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_4046 GBV_ILN_4307 GBV_ILN_4319 GBV_ILN_4700 AR 31 1991 1 03 1-7 |
allfields_unstemmed |
10.1007/BF02325715 doi (DE-627)OLC2058164520 (DE-He213)BF02325715-p DE-627 ger DE-627 rakwb eng 690 VZ Lingaiah, K. verfasserin aut Strength and stiffness of sandwich beams in bending 1991 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Society for Experimental Mechanics, Inc. 1991 Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. Failure Load Sandwich Structure Shear Stiffness Sandwich Beam Flexural Stiffness Suryanarayana, B. G. aut Enthalten in Experimental mechanics Kluwer Academic Publishers, 1961 31(1991), 1 vom: März, Seite 1-7 (DE-627)129593990 (DE-600)240480-1 (DE-576)015086852 0014-4851 nnns volume:31 year:1991 number:1 month:03 pages:1-7 https://doi.org/10.1007/BF02325715 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-UMW SSG-OLC-ARC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_70 GBV_ILN_2004 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_4046 GBV_ILN_4307 GBV_ILN_4319 GBV_ILN_4700 AR 31 1991 1 03 1-7 |
allfieldsGer |
10.1007/BF02325715 doi (DE-627)OLC2058164520 (DE-He213)BF02325715-p DE-627 ger DE-627 rakwb eng 690 VZ Lingaiah, K. verfasserin aut Strength and stiffness of sandwich beams in bending 1991 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Society for Experimental Mechanics, Inc. 1991 Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. Failure Load Sandwich Structure Shear Stiffness Sandwich Beam Flexural Stiffness Suryanarayana, B. G. aut Enthalten in Experimental mechanics Kluwer Academic Publishers, 1961 31(1991), 1 vom: März, Seite 1-7 (DE-627)129593990 (DE-600)240480-1 (DE-576)015086852 0014-4851 nnns volume:31 year:1991 number:1 month:03 pages:1-7 https://doi.org/10.1007/BF02325715 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-UMW SSG-OLC-ARC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_70 GBV_ILN_2004 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_4046 GBV_ILN_4307 GBV_ILN_4319 GBV_ILN_4700 AR 31 1991 1 03 1-7 |
allfieldsSound |
10.1007/BF02325715 doi (DE-627)OLC2058164520 (DE-He213)BF02325715-p DE-627 ger DE-627 rakwb eng 690 VZ Lingaiah, K. verfasserin aut Strength and stiffness of sandwich beams in bending 1991 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Society for Experimental Mechanics, Inc. 1991 Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. Failure Load Sandwich Structure Shear Stiffness Sandwich Beam Flexural Stiffness Suryanarayana, B. G. aut Enthalten in Experimental mechanics Kluwer Academic Publishers, 1961 31(1991), 1 vom: März, Seite 1-7 (DE-627)129593990 (DE-600)240480-1 (DE-576)015086852 0014-4851 nnns volume:31 year:1991 number:1 month:03 pages:1-7 https://doi.org/10.1007/BF02325715 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-UMW SSG-OLC-ARC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_70 GBV_ILN_2004 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_4046 GBV_ILN_4307 GBV_ILN_4319 GBV_ILN_4700 AR 31 1991 1 03 1-7 |
language |
English |
source |
Enthalten in Experimental mechanics 31(1991), 1 vom: März, Seite 1-7 volume:31 year:1991 number:1 month:03 pages:1-7 |
sourceStr |
Enthalten in Experimental mechanics 31(1991), 1 vom: März, Seite 1-7 volume:31 year:1991 number:1 month:03 pages:1-7 |
format_phy_str_mv |
Article |
institution |
findex.gbv.de |
topic_facet |
Failure Load Sandwich Structure Shear Stiffness Sandwich Beam Flexural Stiffness |
dewey-raw |
690 |
isfreeaccess_bool |
false |
container_title |
Experimental mechanics |
authorswithroles_txt_mv |
Lingaiah, K. @@aut@@ Suryanarayana, B. G. @@aut@@ |
publishDateDaySort_date |
1991-03-01T00:00:00Z |
hierarchy_top_id |
129593990 |
dewey-sort |
3690 |
id |
OLC2058164520 |
language_de |
englisch |
fullrecord |
<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">OLC2058164520</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230504082646.0</controlfield><controlfield tag="007">tu</controlfield><controlfield tag="008">200819s1991 xx ||||| 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1007/BF02325715</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)OLC2058164520</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-He213)BF02325715-p</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="082" ind1="0" ind2="4"><subfield code="a">690</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Lingaiah, K.</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Strength and stiffness of sandwich beams in bending</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">1991</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">ohne Hilfsmittel zu benutzen</subfield><subfield code="b">n</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Band</subfield><subfield code="b">nc</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© Society for Experimental Mechanics, Inc. 1991</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Failure Load</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Sandwich Structure</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Shear Stiffness</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Sandwich Beam</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Flexural Stiffness</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Suryanarayana, B. G.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">Experimental mechanics</subfield><subfield code="d">Kluwer Academic Publishers, 1961</subfield><subfield code="g">31(1991), 1 vom: März, Seite 1-7</subfield><subfield code="w">(DE-627)129593990</subfield><subfield code="w">(DE-600)240480-1</subfield><subfield code="w">(DE-576)015086852</subfield><subfield code="x">0014-4851</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:31</subfield><subfield code="g">year:1991</subfield><subfield code="g">number:1</subfield><subfield code="g">month:03</subfield><subfield code="g">pages:1-7</subfield></datafield><datafield tag="856" ind1="4" ind2="1"><subfield code="u">https://doi.org/10.1007/BF02325715</subfield><subfield code="z">lizenzpflichtig</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_OLC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-UMW</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-ARC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-TEC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-PHY</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_11</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_20</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_22</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_23</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_70</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2004</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2014</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2015</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2020</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4046</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4307</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4319</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4700</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">31</subfield><subfield code="j">1991</subfield><subfield code="e">1</subfield><subfield code="c">03</subfield><subfield code="h">1-7</subfield></datafield></record></collection>
|
author |
Lingaiah, K. |
spellingShingle |
Lingaiah, K. ddc 690 misc Failure Load misc Sandwich Structure misc Shear Stiffness misc Sandwich Beam misc Flexural Stiffness Strength and stiffness of sandwich beams in bending |
authorStr |
Lingaiah, K. |
ppnlink_with_tag_str_mv |
@@773@@(DE-627)129593990 |
format |
Article |
dewey-ones |
690 - Buildings |
delete_txt_mv |
keep |
author_role |
aut aut |
collection |
OLC |
remote_str |
false |
illustrated |
Not Illustrated |
issn |
0014-4851 |
topic_title |
690 VZ Strength and stiffness of sandwich beams in bending Failure Load Sandwich Structure Shear Stiffness Sandwich Beam Flexural Stiffness |
topic |
ddc 690 misc Failure Load misc Sandwich Structure misc Shear Stiffness misc Sandwich Beam misc Flexural Stiffness |
topic_unstemmed |
ddc 690 misc Failure Load misc Sandwich Structure misc Shear Stiffness misc Sandwich Beam misc Flexural Stiffness |
topic_browse |
ddc 690 misc Failure Load misc Sandwich Structure misc Shear Stiffness misc Sandwich Beam misc Flexural Stiffness |
format_facet |
Aufsätze Gedruckte Aufsätze |
format_main_str_mv |
Text Zeitschrift/Artikel |
carriertype_str_mv |
nc |
hierarchy_parent_title |
Experimental mechanics |
hierarchy_parent_id |
129593990 |
dewey-tens |
690 - Building & construction |
hierarchy_top_title |
Experimental mechanics |
isfreeaccess_txt |
false |
familylinks_str_mv |
(DE-627)129593990 (DE-600)240480-1 (DE-576)015086852 |
title |
Strength and stiffness of sandwich beams in bending |
ctrlnum |
(DE-627)OLC2058164520 (DE-He213)BF02325715-p |
title_full |
Strength and stiffness of sandwich beams in bending |
author_sort |
Lingaiah, K. |
journal |
Experimental mechanics |
journalStr |
Experimental mechanics |
lang_code |
eng |
isOA_bool |
false |
dewey-hundreds |
600 - Technology |
recordtype |
marc |
publishDateSort |
1991 |
contenttype_str_mv |
txt |
container_start_page |
1 |
author_browse |
Lingaiah, K. Suryanarayana, B. G. |
container_volume |
31 |
class |
690 VZ |
format_se |
Aufsätze |
author-letter |
Lingaiah, K. |
doi_str_mv |
10.1007/BF02325715 |
dewey-full |
690 |
title_sort |
strength and stiffness of sandwich beams in bending |
title_auth |
Strength and stiffness of sandwich beams in bending |
abstract |
Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. © Society for Experimental Mechanics, Inc. 1991 |
abstractGer |
Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. © Society for Experimental Mechanics, Inc. 1991 |
abstract_unstemmed |
Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use. © Society for Experimental Mechanics, Inc. 1991 |
collection_details |
GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-UMW SSG-OLC-ARC SSG-OLC-TEC SSG-OLC-PHY GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_70 GBV_ILN_2004 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_4046 GBV_ILN_4307 GBV_ILN_4319 GBV_ILN_4700 |
container_issue |
1 |
title_short |
Strength and stiffness of sandwich beams in bending |
url |
https://doi.org/10.1007/BF02325715 |
remote_bool |
false |
author2 |
Suryanarayana, B. G. |
author2Str |
Suryanarayana, B. G. |
ppnlink |
129593990 |
mediatype_str_mv |
n |
isOA_txt |
false |
hochschulschrift_bool |
false |
doi_str |
10.1007/BF02325715 |
up_date |
2024-07-03T17:56:23.535Z |
_version_ |
1803581530872741888 |
fullrecord_marcxml |
<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">OLC2058164520</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230504082646.0</controlfield><controlfield tag="007">tu</controlfield><controlfield tag="008">200819s1991 xx ||||| 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1007/BF02325715</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)OLC2058164520</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-He213)BF02325715-p</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="082" ind1="0" ind2="4"><subfield code="a">690</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Lingaiah, K.</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Strength and stiffness of sandwich beams in bending</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">1991</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">ohne Hilfsmittel zu benutzen</subfield><subfield code="b">n</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Band</subfield><subfield code="b">nc</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© Society for Experimental Mechanics, Inc. 1991</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Abstract This investigation is concerned with the experimental versus analytical correlation of the mechanical properties of sandwich-beam specimens. Such sandwich structures are commonly employed in the aircraft industry. Four-point and three-point load tests were conducted on a large number of sandwich-beam specimens, fabricated by using fiber-glass reinforced plastics (both unidirectional and woven-glass cloth) and DTD 685 aluminum alloy for the facings with aluminum honeycomb core and polyurethane foam cores and the indigenously available Araldite as the bonding medium between the core and the facings. The flexural stiffness of the composite sandwich specimens used in this investigation compared favorably with theoretical predictions. The shear stiffness was found to be about 55 percent and 45 percent of the theoretically predicted values for FRP (fiberglass-reinforced-plastic) cloth and FRP unidirectional laminates with aluminum honeycomb core sandwich, respectively. The failure load as determined by experiments was less than the theoretically predicted safe load. There was a loss of strength as well as a steep decrease in the failure load in the case of low density foam core. It was concluded that FRP facing plates with aluminum honeycomb core sandwich structure may be preferred to similar aluminum-alloy facing sandwich construction if high flexural stiffness and shear stiffness properties are required at less cost and weight. Indigenously available Araldite was quite satisfactory for bonding the core to the facings. This investigation has confirmed the importance of experiments in the field of sandwich structures which can effectively replace other conventional uneconomical structural or machine members which are currently in use.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Failure Load</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Sandwich Structure</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Shear Stiffness</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Sandwich Beam</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Flexural Stiffness</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Suryanarayana, B. G.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">Experimental mechanics</subfield><subfield code="d">Kluwer Academic Publishers, 1961</subfield><subfield code="g">31(1991), 1 vom: März, Seite 1-7</subfield><subfield code="w">(DE-627)129593990</subfield><subfield code="w">(DE-600)240480-1</subfield><subfield code="w">(DE-576)015086852</subfield><subfield code="x">0014-4851</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:31</subfield><subfield code="g">year:1991</subfield><subfield code="g">number:1</subfield><subfield code="g">month:03</subfield><subfield code="g">pages:1-7</subfield></datafield><datafield tag="856" ind1="4" ind2="1"><subfield code="u">https://doi.org/10.1007/BF02325715</subfield><subfield code="z">lizenzpflichtig</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_OLC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-UMW</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-ARC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-TEC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-PHY</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_11</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_20</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_22</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_23</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_70</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2004</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2014</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2015</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2020</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4046</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4307</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4319</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4700</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">31</subfield><subfield code="j">1991</subfield><subfield code="e">1</subfield><subfield code="c">03</subfield><subfield code="h">1-7</subfield></datafield></record></collection>
|
score |
7.400259 |