Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading

Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pi...
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	Bharath, K. [verfasserIn] Chikmath, L.

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2017

Schlagwörter:	Lug joints Prognosis Crack growth Fatigue Interference Clearance fits

Anmerkung:	© Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017

Übergeordnetes Werk:	Enthalten in: ISSS Journal of micro and smart systems - [New Delhi] : Springer India, 2017, 6(2017), 1 vom: 10. März, Seite 15-27
Übergeordnetes Werk:	volume:6 ; year:2017 ; number:1 ; day:10 ; month:03 ; pages:15-27

Links:	Volltext

DOI / URN:	10.1007/s41683-017-0002-2

Katalog-ID:	SPR038284022

Internformat


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520			\|a Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology.
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matchkey_str	article:25097997:2017----::rgoiaayiotprdusihnefrnencernei
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publishDate	2017
allfields	10.1007/s41683-017-0002-2 doi (DE-627)SPR038284022 (SPR)s41683-017-0002-2-e DE-627 ger DE-627 rakwb eng Bharath, K. verfasserin (orcid)0000-0002-6024-2402 aut Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading 2017 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017 Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology. Lug joints (dpeaa)DE-He213 Prognosis (dpeaa)DE-He213 Crack growth (dpeaa)DE-He213 Fatigue (dpeaa)DE-He213 Interference (dpeaa)DE-He213 Clearance fits (dpeaa)DE-He213 Chikmath, L. aut Enthalten in ISSS Journal of micro and smart systems [New Delhi] : Springer India, 2017 6(2017), 1 vom: 10. März, Seite 15-27 (DE-627)882382403 (DE-600)2888576-4 2509-7997 nnns volume:6 year:2017 number:1 day:10 month:03 pages:15-27 https://dx.doi.org/10.1007/s41683-017-0002-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 6 2017 1 10 03 15-27
spelling	10.1007/s41683-017-0002-2 doi (DE-627)SPR038284022 (SPR)s41683-017-0002-2-e DE-627 ger DE-627 rakwb eng Bharath, K. verfasserin (orcid)0000-0002-6024-2402 aut Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading 2017 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017 Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology. Lug joints (dpeaa)DE-He213 Prognosis (dpeaa)DE-He213 Crack growth (dpeaa)DE-He213 Fatigue (dpeaa)DE-He213 Interference (dpeaa)DE-He213 Clearance fits (dpeaa)DE-He213 Chikmath, L. aut Enthalten in ISSS Journal of micro and smart systems [New Delhi] : Springer India, 2017 6(2017), 1 vom: 10. März, Seite 15-27 (DE-627)882382403 (DE-600)2888576-4 2509-7997 nnns volume:6 year:2017 number:1 day:10 month:03 pages:15-27 https://dx.doi.org/10.1007/s41683-017-0002-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 6 2017 1 10 03 15-27
allfields_unstemmed	10.1007/s41683-017-0002-2 doi (DE-627)SPR038284022 (SPR)s41683-017-0002-2-e DE-627 ger DE-627 rakwb eng Bharath, K. verfasserin (orcid)0000-0002-6024-2402 aut Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading 2017 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017 Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology. Lug joints (dpeaa)DE-He213 Prognosis (dpeaa)DE-He213 Crack growth (dpeaa)DE-He213 Fatigue (dpeaa)DE-He213 Interference (dpeaa)DE-He213 Clearance fits (dpeaa)DE-He213 Chikmath, L. aut Enthalten in ISSS Journal of micro and smart systems [New Delhi] : Springer India, 2017 6(2017), 1 vom: 10. März, Seite 15-27 (DE-627)882382403 (DE-600)2888576-4 2509-7997 nnns volume:6 year:2017 number:1 day:10 month:03 pages:15-27 https://dx.doi.org/10.1007/s41683-017-0002-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 6 2017 1 10 03 15-27
allfieldsGer	10.1007/s41683-017-0002-2 doi (DE-627)SPR038284022 (SPR)s41683-017-0002-2-e DE-627 ger DE-627 rakwb eng Bharath, K. verfasserin (orcid)0000-0002-6024-2402 aut Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading 2017 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017 Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology. Lug joints (dpeaa)DE-He213 Prognosis (dpeaa)DE-He213 Crack growth (dpeaa)DE-He213 Fatigue (dpeaa)DE-He213 Interference (dpeaa)DE-He213 Clearance fits (dpeaa)DE-He213 Chikmath, L. aut Enthalten in ISSS Journal of micro and smart systems [New Delhi] : Springer India, 2017 6(2017), 1 vom: 10. März, Seite 15-27 (DE-627)882382403 (DE-600)2888576-4 2509-7997 nnns volume:6 year:2017 number:1 day:10 month:03 pages:15-27 https://dx.doi.org/10.1007/s41683-017-0002-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 6 2017 1 10 03 15-27
allfieldsSound	10.1007/s41683-017-0002-2 doi (DE-627)SPR038284022 (SPR)s41683-017-0002-2-e DE-627 ger DE-627 rakwb eng Bharath, K. verfasserin (orcid)0000-0002-6024-2402 aut Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading 2017 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017 Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology. Lug joints (dpeaa)DE-He213 Prognosis (dpeaa)DE-He213 Crack growth (dpeaa)DE-He213 Fatigue (dpeaa)DE-He213 Interference (dpeaa)DE-He213 Clearance fits (dpeaa)DE-He213 Chikmath, L. aut Enthalten in ISSS Journal of micro and smart systems [New Delhi] : Springer India, 2017 6(2017), 1 vom: 10. März, Seite 15-27 (DE-627)882382403 (DE-600)2888576-4 2509-7997 nnns volume:6 year:2017 number:1 day:10 month:03 pages:15-27 https://dx.doi.org/10.1007/s41683-017-0002-2 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_120 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_266 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 6 2017 1 10 03 15-27
language	English
source	Enthalten in ISSS Journal of micro and smart systems 6(2017), 1 vom: 10. März, Seite 15-27 volume:6 year:2017 number:1 day:10 month:03 pages:15-27
sourceStr	Enthalten in ISSS Journal of micro and smart systems 6(2017), 1 vom: 10. März, Seite 15-27 volume:6 year:2017 number:1 day:10 month:03 pages:15-27
format_phy_str_mv	Article
institution	findex.gbv.de
topic_facet	Lug joints Prognosis Crack growth Fatigue Interference Clearance fits
isfreeaccess_bool	false
container_title	ISSS Journal of micro and smart systems
authorswithroles_txt_mv	Bharath, K. @@aut@@ Chikmath, L. @@aut@@
publishDateDaySort_date	2017-03-10T00:00:00Z
hierarchy_top_id	882382403
id	SPR038284022
language_de	englisch
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These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. 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author	Bharath, K.
spellingShingle	Bharath, K. misc Lug joints misc Prognosis misc Crack growth misc Fatigue misc Interference misc Clearance fits Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading
authorStr	Bharath, K.
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topic_title	Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading Lug joints (dpeaa)DE-He213 Prognosis (dpeaa)DE-He213 Crack growth (dpeaa)DE-He213 Fatigue (dpeaa)DE-He213 Interference (dpeaa)DE-He213 Clearance fits (dpeaa)DE-He213
topic	misc Lug joints misc Prognosis misc Crack growth misc Fatigue misc Interference misc Clearance fits
topic_unstemmed	misc Lug joints misc Prognosis misc Crack growth misc Fatigue misc Interference misc Clearance fits
topic_browse	misc Lug joints misc Prognosis misc Crack growth misc Fatigue misc Interference misc Clearance fits
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title	Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading
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title_full	Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading
author_sort	Bharath, K.
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author_browse	Bharath, K. Chikmath, L.
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author-letter	Bharath, K.
doi_str_mv	10.1007/s41683-017-0002-2
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title_sort	prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading
title_auth	Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading
abstract	Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology. © Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017
abstractGer	Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology. © Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017
abstract_unstemmed	Abstract In aircraft structures, a variety of lug joints are casted extensively to couple primary structural components. These lug joints are normally fabricated by a single pin or bolt type of fasteners, which leads to a simple joint that is easy to assemble and disassemble. The lug can act as a pivot since clamping of the joint is normally not allowed or acceptable. However, the elastic stress concentration for attachment lugs is very high, and this high stress concentration at the edge of the hole influences crack initiation and crack growth life. The analysis of these problems becomes more complex when there is a loss of contact between the pin and the lug which ends up in contact stress non-linear moving boundary value problems. Integrity of these lug joints becomes primary concern, since their failure can cause a catastrophic failure of the structure. This has led to mandatory implementation of structural health monitoring (SHM) concept at these censorious locations during the design and operational phase of the flight vehicles. The interference fits in particular, tend to reduce the alternating part of the stress variation at critical locations at the expense of increase in mean stress associated with pre-loading condition. There is a reasonable premise for expecting a better fatigue strength and fatigue life from interference fits. This paper addresses prognostic analysis of both interference and clearance fit lug joints to estimate the residual life of these joints and feed into the analysis of SHM methodology. © Institute of Smart Structures & Systems, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India 2017
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title_short	Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading
url	https://dx.doi.org/10.1007/s41683-017-0002-2
remote_bool	true
author2	Chikmath, L.
author2Str	Chikmath, L.
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doi_str	10.1007/s41683-017-0002-2
up_date	2024-07-03T17:11:44.175Z
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Prognosis analysis of tapered lugs with interference and clearance fits under fatigue loading

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