Kovové letecké konstrukce část 1 Materiály

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Kovov leteck konstrukcest 1Materilypodle podklad autor Hans-Jrgen Schmidt, Bianka Schmidt-BrandeckerAeroStruc Aeronautical EngineeringVladivoj Otenek SVM Praha

upravil Milan Rika

*vodSTRUKTURACHEMICK SLOENVLASTNOSTIVROBNTECHNOLOGIEPOUITAPLIKANTECHNOLOGIEVazby ovlivujc vlastnosti a vvoj materil

*vodMaterilyKovovNekovovSlitiny elezaOstatn slitinySyntetickProdnOcel, litiny,... (r 7,9 g/cm)Lehk kovy (r < 5,0 g/cm)Tk kovy (r > 5,0 g/cm)Kompozity (CFRP), keramika, ...Devo, ke, ...Li (0,5)Mg (1,7) Al (2,7) Ti (4,5)Cu (9,0) Pb (11,3) Pt (21,4) Os (22,5)Hybridn materilysticov kompozity (SiC or Al2O3 + Al alloy)Vlkny vyztuen kovy (Glare: fiberglass + Al)Klasifikace materil

*vodPodl rznch typ materil v dopravnch letadlech

*Pehled typ slitinSlitiny hlinkuAlZnMgCuMnSiAl-CuAl-Cu-MgAl-Mg-SiAl-Zn-MgAl-Zn-Mg-CuAl-SiAl-Si-CuAl-MgAl-Mnstrnut slitinylit slitinyvytvrzovan slitiny

*Znaen tvench slitin hlinku podle pvodnch norem SNRozdlen slitin hlinku a jejich znaen

*Rozdlen slitin hlinku a jejich znaenZnaen tvench slitin hlinku podle International Aluminium Association (AA)

Oznaen slitinyHlavn legujc prvekTypick pedstavitel1XXXistota Al>99,00%10502XXXCu20243XXXMn31034XXXSi40025XXXMg57546XXXMg a Si60617XXXZn70758XXXOstatn prvky (nap. Li)80909XXXspeciln zpracovn, nap. prkov metalurgie-

*Rozdlen slitin hlinku a jejich znaenO - hanF - zvrobyH - deforman zpevnnHXX-odlien stupn deformanho zpevnnW - po rozpoutcm hn (nestabiln stav)T - tepeln zpracovanT1XXX - ochlazen ze zven teploty tven a pirozen strnutT2XXX - ochlazen ze zven teploty tven, tven za studena a pirozen strnutT3XXX po rozpoutcm hn, tven za studena a pirozenm strnutT4XXX - po rozpoutcm hn a pirozenm strnutT5XXX - ochlazen ze zven teploty tven a umle strnutT6XXX - po rozpoutcm hn a umlm strnutT7XXX - po rozpoutcm hn a pestrnut / stabilizaciT8XXX - po rozpoutcm hn, tven za studena a umlm strnutT9XXX - po rozpoutcm hn umlm strnut a tven za studena

SN EN 573-1: Hlink a slitiny hlinku st 1:seln oznaovnZnaen tvench slitin hlinku podle International Aluminium Association (AA)

*1) Slitiny tven 2) Slitiny slvrensk Al-Si, Al-Mg vytvrditeln Al-Cu, Al-Mg-Si Al-Zn nevytvrditeln Al-Mg, Al-Mn Al-Si 3) PM slitiny (prkov metalurgie) 4) KKM (Kompozity s kovovou matric) 5) Sdruen materily (ARALL, GLARE)Rozdlen slitin hlinku a jejich znaen

*Tepeln zpracovnHomogenizan (vysokoteplotn) hn

Odstrann vnitnch pnut

hn na mkko

Rozpoutc hn a vytvrzen

Opakovan tepeln zpracovn u vrobce letadel- z dvodu nedostatench vlastnost- z provoznch dvod (deformace za studena, napklad ohyb nebo prosazen)

*Tepeln zpracovn Rozpoutc hn Homogenizan hn hn na mkko Uml strnut

*Tepeln zpracovnPoznmky

Vhodnou volbou parametr strnut lze zskat rzn kombinace vlastnost. Pro zskn vhodnch vlastnost lze napklad uml strnut provst dvoustupov (napklad u nkterch slitin 7XXX), nebo ho lze provdt pi tvec operaci (creep ageing). Proces strnut me bt vrazn ovlivnn plastickou deformac po rozpoutcm hn. U slitin, kter strnou pirozen (2024) lze proces strnut zastavit (pozdret) umstnm do mrazcho boxu (-18C). Pro omezen vnitnch pnut po rozpoutcm hn je vhodn (zvlt u hmotnch kus) ochlazovat vrobek bu do tepl nebo vrouc vody, nebo lze pout jinho chladcho mdia (glykol). Pro pouit glykolu jako chladcho mdia je nutn dodret takov podmnky, kter zaru e rychlost ochlazovn v celm objemu materilu probhne nadkritickou rychlost.

* Tven slitiny typu Al-Cu ady 2XXX(duraly) AA2024 (AlCu4Mg1)Vytvrzovateln slitinyAA2024

T3: Rozpoutc hn 495C, voda 25-35C, tven za studena, pirozen strnut (4 dny)

T4:Rozpoutc hn 495C, voda 25-35C, pirozen strnut (4 dny) tepeln zpracovn u odbratele

T8: Rozpoutc hn 495C, voda 25-35C, tven za studena, uml strnut 190C/12h

*Tven slitiny Al-Zn ady 7XXX - AA7075 (AlZn6MgCu)Vytvrzovateln slitinyAA7075Rozpoutc hn 475C, voda Pirozen strnut - nepouv seUml strnut (120C/24 hod) T6 (115C/5 hod +165C/15 hod) T73 (115C/5 hod +165C/15 hod) T76Ve stavu T6 m slitina maximln pevnost ale patnou korozn odolnost.

Pestrnut na stavy T7X vedou sice ke zhoren pevnosti ale ke zlepen korozn odolnosti. Ve vvoji jsou dal postupy tepelnho zpracovn.

*Slvrensk slitina A357 T61 (AlSi7Mg) Vstup do motoru700 mm Vstupn dvee Airbus Vytvrzovateln slitinyRozpoutc hn 538C/10h, voda 65-100C, uml strnut 120C/8h+154C/8h

*Pklady pouit typ materilA320

*Pklady pouit typ materilA320 forward fuselage

*Pklady pouit typ materilWelded lower fuselage panelsCFRP pressure bulkheadUpper/side fuselage skin in GLARECenter wing box in CRFPUpper deck floor beams in CRFPTailcone Fwd in CRFPFin box & rudder, horizontal tail plane box & elevators with monolithic CFRPAdvanced aluminum alloys for wing coversThermoplastic fixed leading edgeA380-800 structural materials share60136013GLARE252420247xxxGLARE

*Pklady pouit typ materilCivoln letounyWelded partsSheetT6Al-Mg-Si-CuAA 6013Welded partsSheet, plates, forgings, extrusions, tubes, rodsT6Al-Mg-SiAA 6061Sheet are clad with7072 alloySheet, plates, forgings, extrusions, rodsT6, T79, T76, T74, T73Al-Zn-MgAA 7075, 7175, 7475, 7010, 7050, 7055, 7150, 7349High temperaturesSheetT6/T8Al-Cu-MgAA 2618Damage toleranceSheetT3/T4Al-Cu-MgAA 2524Sheet are clad with1230 alloySheet, thin plates, extrusions, tubesT3/T4Al-Cu-MgAA 2024Wrought alloysComplex geometrySand and investment castingsT6Al-Si-MgA 357Casting alloysPlechyT66013, 6056Svaovan dlyT6Al-Mg-Si6061, 6110AT6, T79, T76, T74, T73Al-Zn-Mg7075, 7175, 7475, 7010, 7040 7050, 7055, 70857150, 7349, 7449pro vysok teplotyPlechyT6/T8Al-Cu-Mg2618Damage tolerancePlechyT3/T4Al-Cu-Mg2524T3/T4Al-Cu-Mg2024Tven slitinyRzn tvaryodlvn do pskuT6Al-Si-MgA 357slvrensk slitinaPlechy, desky, vlisky, trubkyPlechy pltovny slitinou 1230Plechy,desky, trubky, tye, vliskyAl-Mg-Si-CuPlechy,desky, trubky, tyePlechy pltovny slitinou 7072Svaovan dly

*Volba materiluMaterialStatick pevnostnavov p.(do iniciace)Lomov hou.Tuhost (E - modulMr. hmotnostVrobn nkladyCenaCorozn odolnost(stress-corrosion cracking )navov odolnost(Iniciace/propace trhlin)drba opravy inspekn prohldkyhlediska provozuhlediska nvrhunavov p.en trhlinDamage toleranceTechnick poadavky

*Volba materiluTechnical aspectsHlavn trendySouasnostDveV budoucnuZvyovn pevnostiLeh slitinyZvyovn korozn odolnostiSniovn vrobnch nkladZvyovn DT odolnosti

*Volba materiluMat. pro statick zatenVysokopevnostn slitiny (Rm, Rp0,2)7XXX7010 T6XXXtlustostnn dly7075 T6XXXtenkostnn dlyTepeln pravy srovnno podle pevnosti (od max k min):7XXX T76, T74 and T73kompromis pevnost/korozn odolnost 7XXX T76 or T74nejlep pro smykov napt 7XXX T6 or T76Vysokomodulov (ET, EC) Al-Li alloys nap.2024 T3XXX desky, plechy, vkovky7149 T76 vliskySlitiny s vysokou mez kluzu v tlaku (Rc0,2)7149 T76 vlisky7055/7150 T77XX desky, plechy, vkovky7010 T6XX desky, plechy, vkovky7075 T6XX desky, plechy, vkovky

*Mat. pro navov zatenKompromis nava/ en / houevnatost2024 T3XXX desky, plechy, vkovky7475 T73XX desky, plechy6013 T6 HDT desky, plechyKorozn odolnost:Nejlep7XXX T732024 T3(krom vkovk)6XXX(krom 6013)Nejhor7XXX T6XXX 2024 T351(koroze pod naptm)Tvitelnost, svaitelnost:Nejlep5XXX6XXXVolba materilu

*Volba materilu2XXX (Al-Cu) :Vborn houevnatostDobr odolnost navNzk rychlost en trhlin vhodn pro aplikace DT pi tahovm zatenNchylnost k vrstevnat korozi pltovn povrchTypick aplikace:Potahy a podlnky doln sti kdelPotahy trupu a podlnkyPevn nbn hranySloty

Charakteristiky a pouit slitinVrstevnat koroze

*Volba materilu7XXX (Al-Zn)Vy pevnost ne 2XXXNi houevnatost ne 2XXXPomal en trhlin pouit jako vysopevnostn materil pro tahov i tlakov oblasti zatenPouit:Potahy a podlnky horn sti kdelNosnky a ebraPodlnky a pepky trupuNosnky smrovek (ale A340-500/600 = CFRP)Klapky a jejich drhyLyiny sedaekPnky, vzpryCharakteristiky a pouit slitin

* log(da/dN)(mm/cykl)10-32024 T3 clad7475 T75110-410-5Volba materilu2024 T42 clad2524 T3 clad2524 T42 clad7050 T74517040 T74517475 T73517055 T77517449 T7651PlechyobrobkyPorovnn odolnosti rstu trhlinypro K = 20 MPam, R = 0.1 and T-L smr

* Volba materiluKc/Kc20241,000,80,60,40,21,22024 T3 clad7475 T7512024 T42 clad2524 T3 clad2524 T42 clad7050 T74517040 T74517475 T73517055 T77517449 T765110203040KIcMPamPorovnn lomov houevnatistiKc/Kc2024 pro plechy, KIC pro obrobky, T-L direction

*Vliv nehomogenn deformace na strukturu a vlastnostilisovnVrobn deformace kovnvlcovnDeformace u odbrateletvarovnTMZpovrchov pravyVliv technologi na vlastnosti

*Schma technologie vroby vlisk zvytvrzovateln slitiny hlinku Vliv technologi na vlastnosti

*Lisovn PMNEPMVliv technologi na vlastnosti

Damage Tolerance - Methods and Application, DTMA 2011

*ustlen stavkonec epusloit vlisekep: AlCu4Mg1Vloky: AlMg3Lisovn tok materilu lisovac matricVliv technologi na vlastnosti

Damage Tolerance - Methods and Application, DTMA 2011

*Nehomogenita mechanickch vlastnost vliskVliv technologi na vlastnosti

Damage Tolerance - Methods and Application, DTMA 2011

*Nehomogenita a anizotropie vlastnost

Damage Tolerance - Methods and Application, DTMA 2011

*Nehomogenita a anizotropie vlastnostBodov odhad distribun funkce pomoc uspodanho nhodnho vbru{N1 N2 Nn}Hodnota distribun funkce F(Ni)Odhady distribun funkce pomoc vztahPevzato z: Jaap Shijve Fatigue of Structures F(Ni)= i/(n+1)F(Ni)= (i-0,5)/nF(Ni)= (3i-1)/(3n+1)

Damage Tolerance - Methods and Application, DTMA 2011

*Bze BBze AAA7475-T73Nehomogenita a anizotropie vlastnostData: A=99% spolehlivost / 95% confidence Data B =90% / 95%

Damage Tolerance - Methods and Application, DTMA 2011

*Korozn praskn (Stress Corrosion Cracking) Korozn praskn je jev, ke ktermu dochz pi souasnm psoben tahovch napt a koroznho prosted. Jedn se o jev obtn kontrolovateln a pedvdateln. Proto je nutn prevence. Odolnost vi SCC je proto jednm z dleitch parametr pi nvrhu materil pro konstrukn ely. K poruchm vlivem SCC me dochzet i v ppadech, kdy materil nen zatovn (napklad pi skladovn nebo pi peprav).Tahov pnut mohou bt vnesena do materilu rznmi mechanismy: pi vrob (kovn, vlcovn, lisovn, jakkoliv deformace za studena), pi deformaci u uivatele, pi monti, pi spojovn (svaovn, ntovn) a pi obrbn.Vliv technologi na vlastnosti

Damage Tolerance - Methods and Application, DTMA 2011

*Korozn praskn (SCC) SCC je komplexn jev kter je ovlivnn soubn psobcmi koroznmi, mechanickmi a metalurgickmi faktory. Charakteristick pro vskyt a sledovn SCC jsou obtn definovateln vlivy prosted, neznalosti v rozdlen tahovch napt, neznalosti v v mechanismech vzniku a en SCC trhlin a obtn definovateln vliv teploty. Z tchto dvod vyplv obtn kontrola tohoto typu poruen. Proto je zsadn prevence.Pi prevenci s ohledem na SCC je proto rozhodujc:volba vhodn slitiny pro dan umstn v konstrukci, volba takovch technologickch operac, kter minimalizuj vnitn pnut, minimalizace konstruknch vliv a navrhovat takov konstrukn een, kter zohleduje strukturu materilu (anizotropie struktury - tlust desky, ST orientace)Vliv technologi na vlastnosti

Damage Tolerance - Methods and Application, DTMA 2011

*Korozn praskn (SCC) Vlcovan deska ze slitiny AA7075STLTLR p0,2Vliv technologi na vlastnosti

Damage Tolerance - Methods and Application, DTMA 2011

*Rozdlen vybranch slitin hlinku podle odolnosti vi SCC do t skupin (podle ESA ECSS-Q-70-36).Vliv technologi na vlastnostiKorozn praskn (SCC)

Skupina IVysok odolnostSkupina II: Stedn odolnostSkupina III: Nzk odolnost2024-T8, tye2219-T6, T82024-T8, 2124-T8desky2011-T3, T42024-T3, T4 7049, 7149, 7050,7075,7475 Ve v T737049, 7050, 7075, 7175, 7475, 7178Ve v T767075, 7175, 7079, 7178, 7475 Ve v T66XXX vechny stavy1420, 1421 (AlLi)80901441, 1460A356.0, A357.0

Damage Tolerance - Methods and Application, DTMA 2011

*Slitina 7075 T6 (AlZn6MgCu) Nboj jzdnho kola Korozn praskn (SCC) Vliv technologi na vlastnosti

Damage Tolerance - Methods and Application, DTMA 2011

* Nboj kola Korozn st lomuStatick st lomuKorozn st lomuStatick st lomuVkovekVlisekKorozn praskn (SCC)

Damage Tolerance - Methods and Application, DTMA 2011

*Vlastnosti slitinPorovnn slitin 2024 a 2524Chemick sloenAluminum alloys 2xxx

Slit.Procenta zastoupen prvkSiFeCuMnMgCrZnTiZrOst.20240.50.53.8 4.90.3 0.91.2 1.80.10.250.150.20.225240.060.124.0 4.50.45 0.71.2 1.60.050.150.10-0.2

*Vlastnosti slitinPopis:Slitina 2024 s pravou T3xxx je nejvhodnj kompromis pro navu, en trhliny a odolnost kehkmu lomu.hustota materilu r = 2.80 g/cm3.Korozn odolnost: 2024 T3 dobr.Mlo by se zamezit trvalmu namhn u slit. 2024 T351 me vst k mezikrystalick korozi a trhlinm korozn praskn.Al slit. 2024

*Vlastnosti slitinSlit. 2024 T3/T351/T42, pltovan plechData: A=99% spolehlivost / 95% confidence Data B =90% / 95% cDataS = minimln dosahovan hodnotydle dan specifikace

*Vlastnosti slitinSlit. 2024 T3/T351/T42, pltovan plechKt = 2.5Pravdpodobnost poruchy: P=50 %

*Vlastnosti slitinPopis:Al slit. 2524 m shodn mater. vlastnosti jako 2024, kromen trhliny m ni rychlost enlomov houevnatos je o 20 procent vy ne 2024hustota materilu r = 2.80 g/cm3.

Pouit: 2524 se uv tam, kde se dve uvala slit. 2024, avak kde je vyadovna vy odolnost proti en trhliny nebo vy lom. houevnatost.Korozn odolnost:jako 2024Slitina 2524

*Vlastnosti slitinSlit. 2524 T3/T351, pltovan plechspeciln povrch. prava

*Vlastnosti slitinSlit. 2524 T42, plt. plech- spec. povrch. prava

*Vlastnosti slitin20242524da/dn(mm/cykl)K (MPam)Porovnn en trhlin 2024 / 2524 T3/T351 plechR = 0.1

Diagramm3

0.00008292880.0000682051

0.00094450190.0006028313

0.00420102870.0022939393

0.01292516250.0062621315

0.03315521560.0144663554

0.07801933490.0306764544

0.18162232520.0632041026

0.4669650760.134705279

2024 Airbus 2008

2524 Airbus 2008

L-T 2024 + 2524

2024 alt2024 neu2524 Airbus for new method

mm/cyclemm/cyclemm/cycle

10316.22776601680.00006593890.00008292886.82E-05

20632.45553203370.00052539640.00094450196.03E-04

30948.68329805050.00202913020.00420102872.29E-03

401264.91106406740.0062347510.01292516256.26E-03

501581.13883008420.01940511340.03315521561.45E-02

601897.3665961010.1072120820.07801933493.07E-02

702213.5943621179-0.11804528950.18162232526.32E-02

802529.8221281347-0.0620970890.4669650761.35E-01

L-T 2024 + 2524

2024 Airbus 2008

2524 Airbus 2008

T-L 2024 + 2524

2024 alt2024 neu2524 Airbus for new method2524-T3 Alcoa 31.03.06

da/dnda/dnda/dnda/dn

mm/cyclemm/cyclemm/cyclemm/cycle

10316.22776601680.00006593890.00008292886.82E-051.30E-04

20632.45553203370.00052539640.00094450196.03E-045.00E-04

30948.68329805050.00202913020.00420102872.29E-031.50E-03

401264.91106406740.0062347510.01292516256.26E-035.00E-03

501581.13883008420.01940511340.03315521561.45E-021.40E-02

601897.3665961010.1072120820.07801933493.07E-024.00E-02

702213.5943621179-0.11804528950.18162232526.32E-021.00E-01

802529.8221281347-0.0620970890.4669650761.35E-012.50E-01

T-L 2024 + 2524

2024 Airbus 2008

2524 Airbus 2008

Tabelle2

Tabelle3

*Vlastnosti slitin7075, 7475, 7010, 7050, 7150, 7055 a 7349:Slitiny 7xxx

SlitProcent SiFeCuMnMgCrZnTiZrothers70750.40.51.22.00.32.12.90.180.285.15.60.20.25(Ti+Zr)74750.100.121.21.90.061.92.60.180.255.26.20.06-0.1570100.120.151.22.00.12.12.60.055.76.770500.120.152.02.60.11.92.60.045.76.70.060.080.150.1571500.10.152.02.60.051.82.30.047.68.40.60.080.150.1570550.100.152.02.60.051.82.30.047.68.40.060.080.250.1573490.120.151.42.10.21.82.70.100.227.58.70.250.15

*Vlastnosti slitinSrovnn slitin 7xxxoznaen: +...+++ dobr...excelent o uspokojiv - nevhodn!

RmnavaenHou.Korozn odolnostk. prasknPozn.7075T6++O-O--SCC pro smr ST, citlivost na vrstevnatou korozi,aplikace na nov konstrukce nen povolena7075T73+O+++++Do tloutk max.100 mm7475T76++++++++Snen obsah obsah Fe- a Si,- to zvyuje odolnost pro aplikace damage tolerance7010/7050T74++++++++ Poit pro tlouky > 80 mm 7150T76+++++++Vysok pevnost a houevnatost pro tlouky nad >150 mm7055T76++++++++Snen obsah obsah Fe- a Si,-Necitliv na zpsob ochlazovn vysok pevnost7349T76+++O++Necitliv na zpsob ochlazovn velmi vysok pevnost

*Vlastnosti slitinSlitina 7075 T6/T76 pltovan plech

*Vlastnosti slitinSlit. 7075 T6 plt. plechKt = 2.0P=50 %

*Vlastnosti slitinSlit. 7475 T61/T761 plt. plech

*Vlastnosti slitinSlit. 7475 T761 plt. plechKt = 2.5P=50 %

*Vlastnosti slitinSlit. 7010 T7451 nepltovan plech

*Vlastnosti slitinSlit. 7050 T7451 neplt. plech

*Vlastnosti slitinSlit. 7050 T7451 neplt. plechKt = 2.5P=50 %

*Vlastnosti slitinSlit. 7150 T6151/T7751 neplt. plech

*Vlastnosti slitinSlit. 7349/7055 T76511, vlisky

*Vhody slit. 6013 T6 vs. 2024 T3svaitelnosttvarovatelnost pi zprac. T4stajn cenaSlit. 6013Tooling for skin fixingLaser beam 2Sensor joint monitoringLaser beam 1Skin panel and stringersvaovn podlnkPlasma analysisvy mez kluzuvy lom. houevnatostni rychlost en trhlin3 % ni hustotaVlastnosti slitin

*Slitina 6013/6056/6156 T62 pltovan plechVlastnosti slitin

* Pednosti: Snen hmotnosti od 15 do 30%, Odolnost proti proraen Vborn odolnost pi poru Vborn odolnost pi deru blesku Zven odolnost proti en trhlinyNevhody:- Cena- Ni plasticita- Vt anizotropie Vrstven kompozitn materily typu ARALL a GLARE Souasn trendy ve vvoji slitin hlinku pro letectv

* A380-celkem 500m2 Vrstven kompozitn materily GLARE Souasn trendy ve vvoji slitin hlinku pro letectv

* V civilnm letectv je teba plnit hlavn lnky pedpisFAR 25.603 MaterialsThe suitability and durability of materials used for parts, the failure of which could adversely affect safety, must (a) Be established on the basis of experience or tests; (b) Conform to approved specifications (c) Take into account the effects of environmental conditions .FAR 25.605 Fabrication methods (a) The methods of fabrication used must produce a consistently sound structure. . (b) Each new aircraft fabrication method must be substantiated by a test program.FAR 25.613 Material strength properties and material design values (a) Material strength properties must be based on enough tests (b) Material design values must be chosen to minimize the probability of structural failures due to material variability. Aplikovatelnost materil

* Databze datpouv se Metallic Materials Properties Development and Standardization (MMPDS) Handbook (dve MIL-Hdbk. 5)Dostupnost dat

*

Kovov leteck konstrukcest 2Navrhovn dle Damage Tolerancepodle podklad autor Hans-Jrgen Schmidt, Bianka Schmidt-BrandeckerAeroStruc Aeronautical EngineeringVladivoj Otenek SVM Praha

upravil Milan Rika

*Zastoupen pin navovch poruch*Sampath, S.G. and Simpson, D.: Airframe Inspection Reliability Under Field/Depot Conditions, Terms of Reference of AGARD Structures and Materials Panel Proposed Activity SC.77, October 1995.

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Chybn nvrh sousti

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patn kvalita ntovch otvor31Kdlo42

Neznm piny18Trup44

Chybn nvrh sousti16Ocasn plochy3

Korozn dlky a pokozen12Gondoly11

Vnitni vada v materilu23Podvozek14

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Chybn nvrh sousti

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*Lokalizace vskytu poruch*Sampath, S.G. and Simpson, D.: Airframe Inspection Reliability Under Field/Depot Conditions, Terms of Reference of AGARD Structures and Materials Panel Proposed Activity SC.77, October 1995.

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patn kvalita ntovch otvor31Kdlo42

Neznm piny18Trup44

Chybn nvrh sousti16Ocasn plochy3

Korozn dlky a pokozen12Gondoly11

Vnitni vada v materilu23Podvozek14

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Chybn nvrh sousti

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*Oblasti pevnosti a ivotnostiAmplituda napt [MPa]Poet cykl [-]Zkladn pojmy

Rm

oblast

Re

C

*Zkladn pojmy KonstrukcePrimrn konstrukce (Primary structure)je konstrukce, kter pen letov i pozemn zaten, i zaten petlakem. M prakticky toton vznam jako nosn konstrukce.

Sekundrn konstrukce (Secondary structure) je konstrukce, kter pen pouze vzdun nebo setrvan zaten, kter psob vn nebo uvnit tto konstrukce.*Tmata 5, 7 a 8

*Zkladn pojmy Konstrukce*Nosn konstrukce (Airframe)sousti letounu, jejich porucha vn ohroz letoun po pevnostn strnce.sti konstrukce podlhajc prkazu(AAS=Airworthiness affected structure)sousti konstrukce, na kter se vztahuje prkaz letov zpsobilostiTmata 5, 7 a 8

*Zkladn pojmy Konstrukce*

Kritick nosn prvky (CSE=Critical structural elements) (SSI =Significant structural elements)jsou takov prvky, jejich porucha zpsob katastrofick selhn letounu.Hlavn nosn prvky (PSE =Principal structural elements) jsou takov prvky primrn sti konstrukce, kter pispvaj vznamn k penosu letovch i pozemnch zaten a zaten od petlaku. Jejich porucha me zpsobit katastrofick selhn letounu.

Tmata 5, 7 a 8

* Klasifikace konstrukcSekundrn konstrukceSSICel konstrukce= AAS= PSEPrimrn konstrukceZkladn klasifikaceAAS: Airworthiness affected structure (sti u nich se prokazuje letov zpsobilost)PSE:Principal structural element (Hlavn nosn prvky primrn konstrukce)SSI:Significant structural item (Vznan (kritick ) nosn prvky)

* Kritria vbru kritickch ststi penejc vznamn silov tokysti namhan vysokm nominlnm naptmsti s koncentrtory naptsti podroben vysokofrekvennmu zatenSekundrn sti, kter pi poruovn primrnho dlu jsou petovnysti z materilu s vysokou rychlost en trhlinOblasti nchyln k nhodnmu pokozenDly, kter se ukzaly bt kritick pi navovch zkoukch konstrukce

* Kategorie pokozen konstrukceLokln pokozenLocal Damage (LD)Pokozen vce lelementMultiple ElementDamage (MED)Vcensobn pokozen Multiple SiteDamage (MSD)Rozprostrann n. pokozen Widespread FatigueDamage (WFD)

*Zpsoby navrhovn na navu

Konstrukce s bezpenm ivotem (Safe-life) konstrukce mus bt posouzena s ohledem na schopnost vydret opakovan zaten promnn velikosti pedpokldan bhem celho navovho ivota a to bez zjistitelnch trhlin.

Konstrukce bezpen pi porue (Fail-safe) znamen, e konstrukce je navrhovna tak, aby katastrofick selhn nebylo pravdpodobn ani po vzniku navov poruchy, nebo pi zejmm selhn jednoho dleitho nosnho lenu.*VUT FS & SM, datum

*Zpsoby navrhovn na navu*Zpsoby navrhovn na mezn stav NAVY

*Zpsoby navrhovn na navuKonstrukce sppustnm pokozenm (Damage tolerance)konstrukce jako celek je posuzovna pi vnm pokozen navou, koroz, nebo provoznm pokozenm, ke ktermu me dojt v prbhu provoznho ivota letounu, s ohledem na schopnost zbytku konstrukce penst vznamn provozn zaten bez poruchy nebo bez znanch provoznch deformac po dobu do zjitn takovho pokozen.Konstrukce s pomalm enm trhlin (Slow crack growth)materilov a konstrukn opaten nemohou vprovozu zpsobit rychl en trhliny, nebo jejich vzjemn spojovn, take rozvoj trhliny mezi dvma kontrolnmi prohldkami neme zpsobit poruchu.*VUT FS & SM, datum

*Zpsoby navrhovn na navu*Zpsoby navrhovn na mezn stav NAVY

*Zkladn pojmy Penos zatenJednoduch penos zaten (Single load path) psobc zaten je rozloeno pouze na jeden prvek uvnit soustavy a jeho porucha zpsob ztrtu schopnosti penet zaten u sousti, jej je lenem.

Mnohaetn penos zaten (Multiple load path)je toton se staticky neuritou konstrukc, kde pi porue jednoho prvku je psobc zaten bezpen rozloeno na ostatn nosn prvky.

*Tmata 5, 7 a 8

*Vvoj koncepce Safe life, fail safe and damage tolerancePedpisy letov zpsobilosti 1954Comet 1988Aloha 1974MIL-A-83444 1978 FAR 25.571 1998 FAR 25.571 1956 CAR4b.270 1953 CAR 4b.216 20xx NC(trup)Safe Life or Fail SafeDamage Tolerance,(Safe Life pouze pro thla a podvozky)multiple damages, full scale fatigue testsV nvrhuStructural Damage Capability Amend. 96 Amend. 45 yearVvoj pedpis pro certifikace letadel

*Safe Life:(1956 to 1978) *Nepipout vznik trhlinyKlasick metody navyPalmgren/MinerNeuvauje pokozen z vrobyani korozn pokozenZpsoby navrhovn na navuFail Safe:(1956 to 1978)limitn je kritick dlka vady a-critMetody lomov mechanikydundancyStaticky neurit konstrukceSchopnost provozu s poruchou nepedepisuje pravideln kontrolyN a-crit a-detdlkatrhlinyhodin provozuSafe LifeFail Safe

Diagramm4

018.2955201.2826

019.2758202.2847

0.05820.285202.5909

0.642120.5949203.519

1.2421.5375204.4664

1.85222.5061205.4341

2.478723.5018206.423

3.119724.5251207.4342

3.776424.8393207.7433

4.449325.7943208.6805

5.139226.7747209.638

5.846327.7829210.6169

6.57228.0925211.6182

7.31729.0337211.9243

8.082230.0005212.8528

8.867530.9941213.8019

9.674632.0157214.7721

10.504532.3291215.7651

11.35833.2818216.782

12.235334.2597217.0932

13.138335.2637218.0378

14.068335.5716219.0045

15.025736.5069219.9945

16.012537.4651221.0091

17.030238.4477221.3199

17.343139.4559222.2634

39.7648223.2297

40.7028224.2203

41.663225.2334

42.647225.5429

43.6555226.4814

43.9643227.4399

44.9016228.419

45.8609229.4203

46.8424229.7264

47.8477230.6547

48.1552231.6032

49.0886232.5731

50.0441233.5656

51.0227234.582

52.025234.8931

52.3317235.8372

53.2627236.8035

54.215237.7933

55.1896238.808

56.1874239.1188

57.2089240.0627

57.5215241.03

58.47242.0221

59.4399243.0403

60.4322243.3526

61.4478244.3018

61.7582245.2758

62.6999246.277

63.6622246.583

64.646247.5107

65.6521248.4581

65.9596249.4268

66.8919250.4175

67.8436251.4326

68.8159251.7433

69.8095252.6869

70.8252253.6531

71.1359254.6455

72.0786255.6651

73.0425255.9797

74.0282256.9365

75.037257.9353

75.3455258.9933

76.2811

77.2372

78.2147

79.2144

80.237

80.5496

81.4978

82.4666

83.4569

84.4695

84.7789

85.7171

86.6749

87.6534

88.6533

89.6756

89.9879

90.9348

91.9015

92.889

93.8986

94.2072

95.1427

96.0983

97.0746

98.0724

99.0928

99.4046

100.3501

101.3154

102.3016

103.3096

103.6174

104.5507

105.5033

106.476

107.4697

108.4851

108.7952

109.7351

110.6944

111.6738

112.6743

112.9797

113.9053

114.8496

115.8141

116.7997

117.807

118.1148

119.0479

120.0005

120.9735

121.9678

122.9842

123.2948

124.2363

125.1976

126.1794

127.1827

127.4892

128.4181

129.3661

130.3342

131.323

132.3336

132.6422

133.5779

134.533

135.5081

136.5042

137.5228

137.834

138.7778

139.7416

140.7265

141.7333

142.0409

142.9734

143.9256

144.8981

145.892

146.9082

147.2187

148.1603

149.1219

150.1043

151.1087

151.4156

152.3459

153.2959

154.2663

155.2579

156.272

156.5819

157.5216

158.4813

159.4617

160.4636

160.7697

161.6973

162.6443

163.6113

164.5994

165.6094

165.918

166.8535

167.8088

168.7849

169.7825

170.8028

171.1147

172.0604

173.0266

174.0141

175.0242

175.3329

176.2691

177.2254

178.203

179.2028

180.2259

180.5387

181.4869

182.4552

183.4447

184.4564

184.7655

185.7028

186.6601

187.6384

188.6383

189.6612

189.974

190.9227

191.8923

192.8838

193.8985

194.2088

195.1501

196.1124

197.0967

198.1044

198.4126

199.3477

200.3041

0 bis adet

adet bis acrit

acrit bis Ende

R1610L

0 bis a-deta-det bis a-crita-crit bis Ende Rechn.

0.000.000.0039.50

0.0075000.000.0039.50

33075330.000.0639.5580

363078630.000.6440.1421

693081930.001.2440.7400

1023085230.001.8541.3520

1353088530.002.4841.9787

1683091830.003.1242.6197

2013095130.003.7843.2764

2343098430.004.4543.9493

26730101730.005.1444.6392

30030105030.005.8545.3463

33330108330.006.5746.0720

36630111630.007.3246.8170

39930114930.008.0847.5822

43230118230.008.8748.3675

46530121530.009.6749.1746

49830124830.0010.5050.0045

53130128130.0011.3650.8580

56430131430.0012.2451.7353

59730134730.0013.1452.6383

63030138030.0014.0753.5683

66330141330.0015.0354.5257

69630144630.0016.0155.5125

72930147930.0017.0356.5302

73920148920.0017.3456.8431

7689057.7955151890.0018.30

7986058.7758154860.0019.28

8283059.7850157830.0020.29

8372160.0949158721.0020.59

8639461.0375161394.0021.54

8906762.0061164067.0022.51

9174063.0018166740.0023.50

9441364.0251169413.0024.53

9521564.3393170215.0024.84

9762165.2943172621.0025.79

10002666.2747175026.0026.77

10243267.2829177432.0027.78

10315467.5925178154.0028.09

10531968.5337180319.0029.03

10748469.5005182484.0030.00

10964970.4941184649.0030.99

11181471.5157186814.0032.02

11246471.8291187464.0032.33

11441272.7818189412.0033.28

11636173.7597191361.0034.26

11831074.7637193310.0035.26

11889475.0716193894.0035.57

12064876.0069195648.0036.51

12240276.9651197402.0037.47

12415677.9477199156.0038.45

12590978.9559200909.0039.46

12643579.2648201435.0039.76

12801480.2028203014.0040.70

12959281.1630204592.0041.66

13117182.1470206171.0042.65

13274983.1555207749.0043.66

13322283.4643208222.0043.96

13464384.4016209643.0044.90

13606485.3609211064.0045.86

13748486.3424212484.0046.84

13890587.3477213905.0047.85

13933187.6552214331.0048.16

14060988.5886215609.0049.09

14188889.5441216888.0050.04

14316690.5227218166.0051.02

14444591.5250219445.0052.03

14482891.8317219828.0052.33

14597992.7627220979.0053.26

14713093.7150222130.0054.22

14828094.6896223280.0055.19

14943195.6874224431.0056.19

15058196.7089225581.0057.21

15092797.0215225927.0057.52

15196297.9700226962.0058.47

15299898.9399227998.0059.44

15403399.9322229033.0060.43

155069100.9478230069.0061.45

155380101.2582230380.0061.76

156312102.1999231312.0062.70

157244103.1622232244.0063.66

158176104.1460233176.0064.65

159108105.1521234108.0065.65

159387105.4596234387.0065.96

160226106.3919235226.0066.89

161065107.3436236065.0067.84

161904108.3159236904.0068.82

162743109.3095237743.0069.81

163581110.3252238581.0070.83

163833110.6359238833.0071.14

164588111.5786239588.0072.08

165343112.5425240343.0073.04

166098113.5282241098.0074.03

166853114.5370241853.0075.04

167079114.8455242079.0075.35

167759115.7811242759.0076.28

168438116.7372243438.0077.24

169118117.7147244118.0078.21

169797118.7144244797.0079.21

170476119.7370245476.0080.24

170680120.0496245680.0080.55

171292120.9978246292.0081.50

171903121.9666246903.0082.47

172515122.9569247515.0083.46

173126123.9695248126.0084.47

173310124.2789248310.0084.78

173860125.2171248860.0085.72

174410126.1749249410.0086.67

174961127.1534249961.0087.65

175511128.1533250511.0088.65

176061129.1756251061.0089.68

176227129.4879251227.0089.99

176722130.4348251722.0090.93

177217131.4015252217.0091.90

177712132.3890252712.0092.89

178208133.3986253208.0093.90

178356133.7072253356.0094.21

178802134.6427253802.0095.14

179248135.5983254248.0096.10

179694136.5746254694.0097.07

180140137.5724255140.0098.07

180585138.5928255585.0099.09

180719138.9046255719.0099.40

181120139.8501256120.00100.35

181521140.8154256521.00101.32

181923141.8016256923.00102.30

182324142.8096257324.00103.31

182444143.1174257444.00103.62

182805144.0507257805.00104.55

183166145.0033258166.00105.50

183527145.9760258527.00106.48

183889146.9697258889.00107.47

184250147.9851259250.00108.49

184358148.2952259358.00108.80

184683149.2351259683.00109.74

185008150.1944260008.00110.69

185333151.1738260333.00111.67

185658152.1743260658.00112.67

185755152.4797260755.00112.98

186048153.4053261048.00113.91

186340154.3496261340.00114.85

186633155.3141261633.00115.81

186925156.2997261925.00116.80

187218157.3070262218.00117.81

187305157.6148262305.00118.11

187569158.5479262569.00119.05

187832159.5005262832.00120.00

188095160.4735263095.00120.97

188358161.4678263358.00121.97

188622162.4842263622.00122.98

188701162.7948263701.00123.29

188938163.7363263938.00124.24

189174164.6976264174.00125.20

189411165.6794264411.00126.18

189648166.6827264648.00127.18

189719166.9892264719.00127.49

189933167.9181264933.00128.42

190146168.8661265146.00129.37

190359169.8342265359.00130.33

190572170.8230265572.00131.32

190785171.8336265785.00132.33

190849172.1422265849.00132.64

191041173.0779266041.00133.58

191233174.0330266233.00134.53

191425175.0081266425.00135.51

191617176.0042266617.00136.50

191809177.0228266809.00137.52

191866177.3340266866.00137.83

192039178.2778267039.00138.78

192212179.2416267212.00139.74

192384180.2265267384.00140.73

192557181.2333267557.00141.73

192609181.5409267609.00142.04

192764182.4734267764.00142.97

192920183.4256267920.00143.93

193075184.3981268075.00144.90

193231185.3920268231.00145.89

193386186.4082268386.00146.91

193433186.7187268433.00147.22

193573187.6603268573.00148.16

193713188.6219268713.00149.12

193852189.6043268852.00150.10

193992190.6087268992.00151.11

194034190.9156269034.00151.42

194160191.8459269160.00152.35

194286192.7959269286.00153.30

194412193.7663269412.00154.27

194538194.7579269538.00155.26

194664195.7720269664.00156.27

194702196.0819269702.00156.58

194815197.0216269815.00157.52

194928197.9813269928.00158.48

195042198.9617270042.00159.46

195155199.9636270155.00160.46

195189200.2697270189.00160.77

195291201.1973270291.00161.70

195393202.1443270393.00162.64

195495203.1113270495.00163.61

195597204.0994270597.00164.60

195699205.1094270699.00165.61

195729205.4180270729.00165.92

195821206.3535270821.00166.85

195913207.3088270913.00167.81

196005208.2849271005.00168.78

196097209.2825271097.00169.78

196188210.3028271188.00170.80

196216210.6147271216.00171.11

196298211.5604271298.00172.06

196381212.5266271381.00173.03

196464213.5141271464.00174.01

196546214.5242271546.00175.02

196571214.8329271571.00175.33

196645215.7691271645.00176.27

196720216.7254271720.00177.23

196794217.7030271794.00178.20

196868218.7028271868.00179.20

196943219.7259271943.00180.23

196965220.0387271965.00180.54

197032220.9869272032.00181.49

197099221.9552272099.00182.46

197166222.9447272166.00183.44

197233223.9564272233.00184.46

197253224.2655272253.00184.77

197313225.2028272313.00185.70

197373226.1601272373.00186.66

197433227.1384272433.00187.64

197494228.1383272494.00188.64

197554229.1612272554.00189.66

197572229.4740272572.00189.97

197626230.4227272626.00190.92

197680231.3923272680.00191.89

197735232.3838272735.00192.88

197789233.3985272789.00193.90

197805233.7088272805.00194.21

197854234.6501272854.00195.15

197903235.6124272903.00196.11

197951236.5967272951.00197.10

198000237.6044273000.00198.10

198015237.9126273015.00198.41

198059238.8477273059.00199.35

198103239.8041273103.00200.30

198147240.7826273147.00201.28

198190241.7847273190.00202.28

198204242.0909273204.00202.59

198243243.0190273243.00203.52

198283243.9664273283.00204.47

198322244.9341273322.00205.43

198362245.9230273362.00206.42

198401246.9342273401.00207.43

198413247.2433273413.00207.74

198449248.1805273449.00208.68

198484249.1380273484.00209.64

198520250.1169273520.00210.62

198555251.1182273555.00211.62

198566251.4243273566.00211.92

198598252.3528273598.00212.85

198630253.3019273630.00213.80

198662254.2721273662.00214.77

198694255.2651273694.00215.77

198726256.2820273726.00216.78

198736256.5932273736.00217.09

198764257.5378273764.00218.04

198793258.5045273793.00219.00

198822259.4945273822.00219.99

198851260.5091273851.00221.01

198859260.8199273859.00221.32

198885261.7634273885.00222.26

198911262.7297273911.00223.23

198937263.7203273937.00224.22

198963264.7334273963.00225.23

198971265.0429273971.00225.54

198994265.9814273994.00226.48

199017266.9399274017.00227.44

199041267.9190274041.00228.42

199064268.9203274064.00229.42

199071269.2264274071.00229.73

199092270.1547274092.00230.65

199113271.1032274113.00231.60

199134272.0731274134.00232.57

199155273.0656274155.00233.57

199176274.0820274176.00234.58

199182274.3931274182.00234.89

199201275.3372274201.00235.84

199220276.3035274220.00236.80

199239277.2933274239.00237.79

199258278.3080274258.00238.81

199264278.6188274264.00239.12

199281279.5627274281.00240.06

199298280.5300274298.00241.03

199315281.5221274315.00242.02

199332282.5403274332.00243.04

199337282.8526274337.00243.35

199352283.8018274352.00244.30

199367284.7758274367.00245.28

199383285.7770274383.00246.28

199387286.0830274387.00246.58

199401287.0107274401.00247.51

199415287.9581274415.00248.46

199429288.9268274429.00249.43

199442289.9175274442.00250.42

199456290.9326274456.00251.43

199460291.2433274460.00251.74

199473292.1869274473.00252.69

199485293.1531274485.00253.65

199498294.1455274498.00254.65

199510295.1651274510.00255.67

199514295.4797274514.00255.98

199525296.4365274525.00256.94

199536297.4353274536.00257.94

199547298.4933274547.00258.99

R1610L

0 bis adet

adet bis acrit

acrit bis Ende

R1610L (2)

0 bis a-deta-det bis a-crita-crit bis Ende Rechn.

0.000.000.0039.50

0.0075000.000.0039.50

33075330.000.0639.5580

363078630.000.6440.1421

693081930.001.2440.7400

1023085230.001.8541.3520

1353088530.002.4841.9787

1683091830.003.1242.6197

2013095130.003.7843.2764

2343098430.004.4543.9493

26730101730.005.1444.6392

30030105030.005.8545.3463

33330108330.006.5746.0720

36630111630.007.3246.8170

39930114930.008.0847.5822

43230118230.008.8748.3675

46530121530.009.6749.1746

49830124830.0010.5050.0045

53130128130.0011.3650.8580

56430131430.0012.2451.7353

59730134730.0013.1452.6383

63030138030.0014.0753.5683

66330141330.0015.0354.5257

69630144630.0016.0155.5125

72930147930.0017.0356.5302

73920148920.0017.3456.8431

7689057.7955151890.0018.30

7986058.7758154860.0019.28

8283059.7850157830.0020.29

8372160.0949158721.0020.59

8639461.0375161394.0021.54

8906762.0061164067.0022.51

9174063.0018166740.0023.50

9441364.0251169413.0024.53

9521564.3393170215.0024.84

9762165.2943172621.0025.79

10002666.2747175026.0026.77

10243267.2829177432.0027.78

10315467.5925178154.0028.09

10531968.5337180319.0029.03

10748469.5005182484.0030.00

10964970.4941184649.0030.99

11181471.5157186814.0032.02

11246471.8291187464.0032.33

11441272.7818189412.0033.28

11636173.7597191361.0034.26

11831074.7637193310.0035.26

11889475.0716193894.0035.57

12064876.0069195648.0036.51

12240276.9651197402.0037.47

12415677.9477199156.0038.45

12590978.9559200909.0039.46

12643579.2648201435.0039.76

12801480.2028203014.0040.70

12959281.1630204592.0041.66

13117182.1470206171.0042.65

13274983.1555207749.0043.66

13322283.4643208222.0043.96

13464384.4016209643.0044.90

13606485.3609211064.0045.86

13748486.3424212484.0046.84

13890587.3477213905.0047.85

13933187.6552214331.0048.16

14060988.5886215609.0049.09

14188889.5441216888.0050.04

14316690.5227218166.0051.02

14444591.5250219445.0052.03

14482891.8317219828.0052.33

14597992.7627220979.0053.26

14713093.7150222130.0054.22

14828094.6896223280.0055.19

14943195.6874224431.0056.19

15058196.7089225581.0057.21

15092797.0215225927.0057.52

15196297.9700226962.0058.47

15299898.9399227998.0059.44

15403399.9322229033.0060.43

155069100.9478230069.0061.45

155380101.2582230380.0061.76

156312102.1999231312.0062.70

157244103.1622232244.0063.66

158176104.1460233176.0064.65

159108105.1521234108.0065.65

159387105.4596234387.0065.96

160226106.3919235226.0066.89

161065107.3436236065.0067.84

161904108.3159236904.0068.82

162743109.3095237743.0069.81

163581110.3252238581.0070.83

163833110.6359238833.0071.14

164588111.5786239588.0072.08

165343112.5425240343.0073.04

166098113.5282241098.0074.03

166853114.5370241853.0075.04

167079114.8455242079.0075.35

167759115.7811242759.0076.28

168438116.7372243438.0077.24

169118117.7147244118.0078.21

169797118.7144244797.0079.21

170476119.7370245476.0080.24

170680120.0496245680.0080.55

171292120.9978246292.0081.50

171903121.9666246903.0082.47

172515122.9569247515.0083.46

173126123.9695248126.0084.47

173310124.2789248310.0084.78

173860125.2171248860.0085.72

174410126.1749249410.0086.67

174961127.1534249961.0087.65

175511128.1533250511.0088.65

176061129.1756251061.0089.68

176227129.4879251227.0089.99

176722130.4348251722.0090.93

177217131.4015252217.0091.90

177712132.3890252712.0092.89

178208133.3986253208.0093.90

178356133.7072253356.0094.21

178802134.6427253802.0095.14

179248135.5983254248.0096.10

179694136.5746254694.0097.07

180140137.5724255140.0098.07

180585138.5928255585.0099.09

180719138.9046255719.0099.40

181120139.8501256120.00100.35

181521140.8154256521.00101.32

181923141.8016256923.00102.30

182324142.8096257324.00103.31

182444143.1174257444.00103.62

182805144.0507257805.00104.55

183166145.0033258166.00105.50

183527145.9760258527.00106.48

183889146.9697258889.00107.47

184250147.9851259250.00108.49

184358148.2952259358.00108.80

184683149.2351259683.00109.74

185008150.1944260008.00110.69

185333151.1738260333.00111.67

185658152.1743260658.00112.67

185755152.4797260755.00112.98

186048153.4053261048.00113.91

186340154.3496261340.00114.85

186633155.3141261633.00115.81

186925156.2997261925.00116.80

187218157.3070262218.00117.81

187305157.6148262305.00118.11

187569158.5479262569.00119.05

187832159.5005262832.00120.00

188095160.4735263095.00120.97

188358161.4678263358.00121.97

188622162.4842263622.00122.98

188701162.7948263701.00123.29

188938163.7363263938.00124.24

189174164.6976264174.00125.20

189411165.6794264411.00126.18

189648166.6827264648.00127.18

189719166.9892264719.00127.49

189933167.9181264933.00128.42

190146168.8661265146.00129.37

190359169.8342265359.00130.33

190572170.8230265572.00131.32

190785171.8336265785.00132.33

190849172.1422265849.00132.64

191041173.0779266041.00133.58

191233174.0330266233.00134.53

191425175.0081266425.00135.51

191617176.0042266617.00136.50

191809177.0228266809.00137.52

191866177.3340266866.00137.83

192039178.2778267039.00138.78

192212179.2416267212.00139.74

192384180.2265267384.00140.73

192557181.2333267557.00141.73

192609181.5409267609.00142.04

192764182.4734267764.00142.97

192920183.4256267920.00143.93

193075184.3981268075.00144.90

193231185.3920268231.00145.89

193386186.4082268386.00146.91

193433186.7187268433.00147.22

193573187.6603268573.00148.16

193713188.6219268713.00149.12

193852189.6043268852.00150.10

193992190.6087268992.00151.11

194034190.9156269034.00151.42

194160191.8459269160.00152.35

194286192.7959269286.00153.30

194412193.7663269412.00154.27

194538194.7579269538.00155.26

194664195.7720269664.00156.27

194702196.0819269702.00156.58

194815197.0216269815.00157.52

194928197.9813269928.00158.48

195042198.9617270042.00159.46

195155199.9636270155.00160.46

195189200.2697270189.00160.77

195291201.1973270291.00161.70

195393202.1443270393.00162.64

195495203.1113270495.00163.61

195597204.0994270597.00164.60

195699205.1094270699.00165.61

195729205.4180270729.00165.92

195821206.3535270821.00166.85

195913207.3088270913.00167.81

196005208.2849271005.00168.78

196097209.2825271097.00169.78

196188210.3028271188.00170.80

196216210.6147271216.00171.11

196298211.5604271298.00172.06

196381212.5266271381.00173.03

196464213.5141271464.00174.01

196546214.5242271546.00175.02

196571214.8329271571.00175.33

196645215.7691271645.00176.27

196720216.7254271720.00177.23

196794217.7030271794.00178.20

196868218.7028271868.00179.20

196943219.7259271943.00180.23

196965220.0387271965.00180.54

197032220.9869272032.00181.49

197099221.9552272099.00182.46

197166222.9447272166.00183.44

197233223.9564272233.00184.46

197253224.2655272253.00184.77

197313225.2028272313.00185.70

197373226.1601272373.00186.66

197433227.1384272433.00187.64

197494228.1383272494.00188.64

197554229.1612272554.00189.66

197572229.4740272572.00189.97

197626230.4227272626.00190.92

197680231.3923272680.00191.89

197735232.3838272735.00192.88

197789233.3985272789.00193.90

197805233.7088272805.00194.21

197854234.6501272854.00195.15

197903235.6124272903.00196.11

197951236.5967272951.00197.10

198000237.6044273000.00198.10

198015237.9126273015.00198.41

198059238.8477273059.00199.35

198103239.8041273103.00200.30

198147240.7826273147.00201.28

198190241.7847273190.00202.28

198204242.0909273204.00202.59

198243243.0190273243.00203.52

198283243.9664273283.00204.47

198322244.9341273322.00205.43

198362245.9230273362.00206.42

198401246.9342273401.00207.43

198413247.2433273413.00207.74

198449248.1805273449.00208.68

198484249.1380273484.00209.64

198520250.1169273520.00210.62

198555251.1182273555.00211.62

198566251.4243273566.00211.92

198598252.3528273598.00212.85

198630253.3019273630.00213.80

198662254.2721273662.00214.77

198694255.2651273694.00215.77

198726256.2820273726.00216.78

198736256.5932273736.00217.09

198764257.5378273764.00218.04

198793258.5045273793.00219.00

198822259.4945273822.00219.99

198851260.5091273851.00221.01

198859260.8199273859.00221.32

198885261.7634273885.00222.26

198911262.7297273911.00223.23

198937263.7203273937.00224.22

198963264.7334273963.00225.23

198971265.0429273971.00225.54

198994265.9814273994.00226.48

199017266.9399274017.00227.44

199041267.9190274041.00228.42

199064268.9203274064.00229.42

199071269.2264274071.00229.73

199092270.1547274092.00230.65

199113271.1032274113.00231.60

199134272.0731274134.00232.57

199155273.0656274155.00233.57

199176274.0820274176.00234.58

199182274.3931274182.00234.89

199201275.3372274201.00235.84

199220276.3035274220.00236.80

199239277.2933274239.00237.79

199258278.3080274258.00238.81

199264278.6188274264.00239.12

199281279.5627274281.00240.06

199298280.5300274298.00241.03

199315281.5221274315.00242.02

199332282.5403274332.00243.04

199337282.8526274337.00243.35

199352283.8018274352.00244.30

199367284.7758274367.00245.28

199383285.7770274383.00246.28

199387286.0830274387.00246.58

199401287.0107274401.00247.51

199415287.9581274415.00248.46

199429288.9268274429.00249.43

199442289.9175274442.00250.42

199456290.9326274456.00251.43

199460291.2433274460.00251.74

199473292.1869274473.00252.69

199485293.1531274485.00253.65

199498294.1455274498.00254.65

199510295.1651274510.00255.67

199514295.4797274514.00255.98

199525296.4365274525.00256.94

199536297.4353274536.00257.94

199547298.4933274547.00258.99

R1610L (2)

0 bis adet

adet bis acrit

acrit bis Ende

Zpsoby navrhovn na navuInterval prohldek=N / kDamage Tolerance*

*Zpsoby navrhovn na navuPoruen hornho zvsu vlivem navyUtren vodorovn ocasn plochy chybn aplikovan isnpekceNevhodn vbr lenu pro ffail-safe koncepcidoln zvshorn zvs

fail safekomponentzadn nosnk(3 oka)iniciace trhlinyPklad selhn filosofie safe life nehoda v Lusace 1977

*Zpsoby navrhovn na navu area without scratchesarea with scratchesdoublerouter fuselage skinStringer 11RHdoor panelpodln trhlina 950 mmPklady nespnch een do r. 1978)

Safe Life Design (FAR 25.571)Safe life, bezp. k=4Vznik poruchy poDvod poruchyA/C typeDrakKC-135Doln potah kdla13 000 h1 000 5 000 h(14 ppad)Pokozen pi vrob nebo provozuF5Koen kdla4 000 h1 900 h(1 ppad)F111Centropln4 000 h105 h (1 ppad)A300(fatigue)Spojen trupu48 000 C(factor 2 in test)22 800 C(1 ppad)Pokozen pidrb

*Uren intervalu periodickch prohldek*O em je DT?Tma 4

Graf2

0.4

0.4

0.4

0.45

0.5

0.6

0.7

0.94

1.29

2

3.3

4.8

8

D

okamik zjitn trhliny

rstov kivkatrhliny

a1

a2

a3

a4

I1

I2

I3

I4

D I

D I

D I

Id

Icr

acr

ad

letov hodiny

dlka trhliny (mm)

List1

Data pro graf ze str.51

xy

090

294

597

898.5

1099

12100

100105

110110

120120

122125

125132

128145

130160

&A

Strana &P

List1

0

0

0

0

0

0

0

0

0

0

0

0

0

&A

Strana &P

Nz

Nf

eh

List2

00

12

24

36

48

59

69.5

109.9

129.8

159.15

168.3

177.3

185.9

194.4

202.9

211.4

22-0.1

23-1.6

24-3.1

25-4.6

&A

Strana &P

List2

0

2

4

6

8

9

9.5

9.9

9.8

9.15

8.3

7.3

5.9

4.4

2.9

1.4

-0.1

-1.6

-3.1

-4.6

&A

Strana &P

srez

sp

N

List3

1543.5

10543

100542

1000525

10000490

100000434

1000000357

&A

Strana &P

List3

0

0

0

0

0

0

0

&A

Strana &P

Nf [cykl]

Napt [MPa]

Isotropn skladba - hladk tlesa mjiv tah

List4

11.18

101.18

1001.18

10001.175

100001.14

1000001.06

10000000.94

100000000.79

1000000000.6

&A

Strana &P

List4

0

0

0

0

0

0

0

0

0

&A

Strana &P

Nf [cykl]

Beta

Isotropn skladba - stedov otvor 6 mm a okraj. vruby 6 mm

List5

00

50001

100002

150003

200004.5

300006.7

3670010

4140013

4520016

4990022

5270028.7

00

500001.458

1000003.2805

1500005.103

2000007.29

2500009.8415

30000013.5

35000018.6

394500240.9

&A

Strana &P

List5

00

00

00

00

00

00

00

00

00

0

0

&A

Strana &P

2024-T3t=2 mm

3/2 Glare 3

poet kmit

polovin dlka trhliny [mm]

List6

000.4

100010.4

200020.4

300030.45

400040.5

500050.6

600060.7

700070.94

800081.29

900092

10000103.3

1080010.84.8

12000128

&A

Strana &P

List6

&A

Strana &P

D

okamik zjitn trhliny

rstov kivkatrhliny

a1

a2

a3

a4

I1

I2

I3

I4

D I

D I

D I

Id

Icr

acr

ad

letov hodiny

dlka trhliny (mm)

List7

&A

Strana &P

List8

&A

Strana &P

List9

&A

Strana &P

*Zpsoby navrhovn na navusuccessful:Rhy iniciovaly korozi a nsledn navov defektRst trhliny, zastavil se na zastavovach z Al slitinyzastavova trhliny lrhynflientov spojerhy od noe pi ezn fliepepkaNehoda: vznik trhliny v trupu - dekompresePklad spn funkce DT

* Klasifikace konstrukcPokozen by mla bt snadno detekovateln a doloena pomalm enm defektu nebo schopnost ho zabrzditSingle load path je ppustn, ale nedeoporuuje se. Dal pedpisy ho omez v pouvnSingle load path structure - Jednoduch penos zaten

* Trhlina je dekovna a me se it i v dalch (vnjch) stech (nap. v potahu po porue podlnku), doloit pomal en a detekovatelnost po porue primrnho lenu; na intern prvek omezen nevztahujeKlasifikace konstrukcNvrh vede k relativn krtkm asm prohldek, lze prodluovat metodami monitorovn stavu konstrukce SHM. Multiple load path structure mnohoetn penos zaten

* Klasifikace konstrukcMLP nedetekovateln ped poruchou primrn stiPedpoklad: Trhlina v primrn sti nebude odhalena dve, ne se cel prvek poru. Interval prohldek determinuje doba en trhliny v sekundrnm lenu.Aplikace pro mal a doplkov dly: zvsy, pdavn oka, kovn dve aj.

* Klasifikace konstrukcNvrh umouje del periody prohldek nebo vy zaten.Doporuuje se MLP detekovateln ped poruchou primrn stiPedpoklad: Trhlina v primrn sti bude odhalena dve, ne se cel prvek poru. Interval prohldek determinuje doba en trhliny od nalezen defektu

* Oblasti uplatnn DTTypick pklady hlavnch dl konstrukce podlehajcm DTpodle pedpisu AC 25.571-1CKdlo a ocasn plochydc plochy, nbn klapky, klapky a jejich mechanick systmy a psluenstv (zvsy, drhy a psluenstv); Panely s integrln vztuhou - podlnky; Spoje primrnch dl; Zvsy; Potahy a zeslen kolem vez nebo spoj; Panely s podlnky; sti nosnk, pekryty nosnk;

* TrupPepky a potah; Rmy dve;Kabina- okna pilot; Tlakov pepka; Potahy a rmy okolo vztuh otvor a dvek trupu;Potahy a spoje potahu od tench napt; Potahy a spoje potahu od ohybovch napt draku; Zvsy, rmy, zmky dveRmy okenPodvozek a jeho sti - dnes jedin st pro aplikovatelnost safe-lifePipojen motor

Oblasti uplatnn DT

* Pklady Fail-safeZvsy kdel na trupuC77pianov zvs dve pro cargo7175 T73511Ti 6Al4V

*Damage tolerant designdlka trhlinykritick dlka trhlinymin. detekovateln t.prhIntervalbezpen doba enivotNvrhov zatenLimitn (max. provozn)doba provozuInterval

*Damage tolerant design - pkladZbytkov pevnost a doba en me bt prodlouena sprvnm dimenzovnm podlnk:tuhostn pomr: = A*EStr/Wt*Eskin (US) = A*EStr/(A*EStr+WtEskin) (Evropa)panel s podlnkyDoporuuje se pout mater. s vy pevnost (nap. potah: 2024 nebo 2524T3, podlnk: 7xxx). A navrhnout pomr 0.25 (pro panely trupu)

*Damage tolerant design - pklad 4 rzn technologie- 2 kategorie: spojovan:NtovnLepenObrbn nebo protlaovnSvaovanIntegrovan:Spojen potah podlnky

* Damage tolerant design - pkladPotah2024, 2524, 7475Podlnk2024, 7075, 73497055pepka2024, 7075ntMezivrstvasvarpotah6013, 6056podlnk6110, 6056pepka2024, 7075SpojovanSvaovandrt LBW: AlMgSi12

*Damage tolerant designVliv ntovanch podlnk na en trhlinypanel s podlnky

* Damage tolerant designVliv integrlnch podlnk na en trhlinypanel s podlnkypanel bez vztuh

*Damage tolerant design Zbytkov pevnost pro vyztuen panelNapt pro iniciaci trhliny v panelu bez vztuhy

*Damage tolerant design-pkladen trhlin zpomaluj zastavovae trhlin (crack stoppers or crack retarders). Dv monosti eenKruhov vztu kolem celho trupu. Zabrzd trhliny, kter by se rozvjely z ntovch spoj v jej ad i mimo ni.Lokln vztuhy, kter zbrzd trhliny pi en v ntovm spojiTrup pi namhn petlakem

*Damage tolerant design - pkladCl: zamezit vzniku trhliny pes dv pole trupuLepen pruhy z GLARE pod ntov pipojen pepek zbrzd podln trhlinyReziduln pevnost:potah1.6 mm , mater. 2024, 2524, 2198 2199vztuha: GLARE (tlouka 1.4 mm, ka 60 mm)trhlina pes 2 pole(e.g. two-bay crack)Allowable stress100 %120 - 130 %bez vztuhs vztuhouvztuha (zastavova)

Diagramm1

10000125A330 incl. A340 WV027

A330

straps

100no strap

0

0

0

125with strap

straps

A330 incl. A340 WV027A330 incl. A340 WV027A330 incl. A340 WV027A330 incl. A340 WV027A330 incl. A340 WV027

A330

*Spojovan: ntovan nebo lepenIntegrln: obroben, protlaovanstage 1stage 2stage 3stage 1stage 2stage 3spojovan nebo integrln proveden me mt jin mechanismus rozvoje defektu:trhlina se neroz do podlnku

trhlina se rozdvoj na podlnk a potahRozvtven trhlinyDamage tolerant design - pklady

*smr rstuZastavovae trhlin v podlnm spoji:trhlina zmn smr en, kdy doshne vztuhy Trhlina na vnj vrstv se stane viditelnou (mimo NDT metody)Mechanismus byl oven testyZmna smru enDamage tolerant design - pklady

* Failure detectabilityDetectable crack length for visual inspection to meet MSG3

*Detekovatelnost trhlinDetekovateln trhliny pi vizulnch prohldkch podle MSG3(Maintenance steering group 3)LDET = LVIS + LHLVIS = LBAS x (gauge factor) x (edge factor)LVIS: je dlka urovan dle MSG3LDET: dlka detekovateln trhliny je spotena podle vztahuLDETLVISLHLCRITNIntervalI =N/jFCL

*95(95)100Pravdpodobnost detekce % dlka trhliny (mm)1234567891090806050402050HFECXRMPVISLPUSLFECHFEC(r)(rotating probe)Detekovatelnou dlku trhliny pro danou NDT uruje PoD kivkaTyto kivky jsou platn pouze pro dan ppad, nelze aplikovat obecn. Doporuuje se pravdpodobnost objeven trhliny 90 % a interval spolehlivosti (confidence level) of 95 % .Legenda nsledujeDetekovatelnost trhlin

* Detekovatelnost trhlinNDT metody

* Abbreviations and symbolsAPermanent strain at rupturea Crack lengthAASAirworthiness affected structureACAdvisory circular (US)AFRPAramid fiber reinforced plasticAlAluminumAl-LiAluminum-LithiumAlMgScAluminum-Magnesium-ScandiumAlMgSiAluminum-Magnesium-Silicium

CAConstant amplitudeCARCivil air regulationsCCTCenter cracked tension specimenCFRPCarbon fiber reinforced plasticCrChromiumCuCopper

DFatigue damageDSGDesign service goalDTDamage tolerance

EYoungs modulus (tension)ECEddy currentEC-HF/MFEddy current high frequency / medium frequencyEC-LFEddy current low frequency

* Abbreviations and symbolsFAAFederal aviation administrationFARFederal aviation regulations (US)FCFlight cycleFCGFatigue crack growthF&DTFatigue and damage toleranceFeIronFH, FhFlight hoursFLGForward landing gearFMLFiber metal laminateFRFrameFwd.Forward

GFRPGlass fiber reinforced plasticHFECHigh frequency eddy current (NDT inspection method)

IInspection intervaljScatter factorLLongitudinal directionLFECLow frequency eddy current (NDT inspection method)LHLeft handLiLithiumLPLiquid penetrant (NDT inspection method)LTLongitudinal transverse direction

* Abbreviations and symbols MEDMultiple element damageMFECMedium frequency eddy current (NDT inspection method)MgMagnesiumMILUS military standardMLDMultiple local damageMLGMain landing gearMMPDS Metallic Materials Properties Development and Standardization MnManganeseMPMagnetic particle (NDT inspection method)MSDMultiple site damageMSG3Maintenance steering group 3MTMid cracked tension specimenN, nLife, number of cycles or number of flightsNaClSodium chlorideNDTNon destructive testing

OsOsmiumPbLeadPODProbability of detectionPSEPrinciple structural elementPtPlatinum

* Abbreviations and symbolsRRatio of minimum to maximum stress (load) of a stress (load) cycleRHRight handsStandard deviationScScandiumSCCStress corrosion crackingSiSilicium (Silicon)SiCSilicium CarbideSN, S-NStress versus life data (diagram or curve)SSIStructural significant itemSTShort transverse directionSTRStringer

TTransverse directionTScatterTiTitanium

USUltrasonic (NDT inspection method)

VAVariable amplitude

WFDWidespread fatigue damage

X-rayX-ray radiation (NDT inspection method)

ZnZincZrZirconium

* Abbreviations and symbolsaeEffective crack extensionKRange of stress intensity factor (Kmax Kmin)Stiffness ratioPoisson ratioDensity StressmMean stressmaxMaximum stressminMinimum stressaipinitial crack length in primary load pathaisinitial crack length in secondary load pathda/dNCrack growth rate (crack growth per load cycle)DFMiner factorDtotalTotal fatigue damageEcYoungs modulus compression Et, EYoungs modulus tensionjLScatter factor on lifeKcFracture toughness for thin materialKIcFracture toughness for thick materialKeEffective stress intensity factorKtStress concentration factorL-TLongitudinal transverse direction (Stress: longitudinal, crack: transverse)

* Abbreviations and symbolsRbru = BUSBearing ultimate strengthRbry = BYSBearing yield strengthRc0,2 = FTY = TYSCompression yield strengthRm = FTU = TUSTensile ultimate strengthRp0,2 = FTY = TYSTensile yield strengthRsu = SUSShear ultimate strengthR50% Risk factor due to number of specimens for SN-dataTScatter T-LTransverse longitudinal direction (Stress: transverse, crack: longitudinal)XReduction factor due to number of fatigue critical locations

VUT FS & SM, 25.4.2011*VUT FS & SM, Blok5-20.4.2011VUT FS & SM, 25.4.2011*VUT FS & SM, Blok5-20.4.2011VUT FS & SM, 25.4.2011*VUT FS & SM, Blok5-20.4.2011VUT FS & SM, 25.4.2011*VUT FS & SM, Blok5-20.4.2011