Приказ основних података о документу
Eksperimentalno određivanje zamornogh veka duraluminijumske ramenjače krila
Aircraft duraluminum wing spar fatigue testing
dc.creator | Petrašinović, Nikola | |
dc.creator | Petrašinović, Danilo | |
dc.creator | Rašuo, Boško | |
dc.creator | Milković, Dragan | |
dc.date.accessioned | 2022-09-19T18:12:17Z | |
dc.date.available | 2022-09-19T18:12:17Z | |
dc.date.issued | 2017 | |
dc.identifier.issn | 1451-2092 | |
dc.identifier.uri | https://machinery.mas.bg.ac.rs/handle/123456789/2597 | |
dc.description.abstract | U radu je prikazana eksperimentalna analiza širenja zamorne prsline u strukturalnom delu vazduhoplovne konstrukcije pod cikličnim opterećenjem. Cilj eksperimentalne analize je da se odredi stvarni zamorni vek ramenjače napravljene od aluminijuma 2024-T3. Ispitna instalacija, za ispitivanje zamornih karakteristika vazduhoplovnih konstrukcija, sopstvene izrade prikazana je u potpunosti. Ispitni uzorak korišćen u radu napravljen je isključivo za ispitivanje na zamor. Rezultati zamornog ispitivanja prikupljeni su najsavremenijom opremom za akviziciju podataka. Primenjena opterećenja, kao i prikupljeni rezultati su detaljno izloženi u tekstu. Na osnovu prethodno sprovedenih istraživanja, doneti su zaključci o dobijenim rezultatima eksperimentalne analize kao i uporedna analiza eksperimentalne i savremene numeričke metode. Na kraju rada date su smernice u kom pravcu bi trebala da idu dalja eksperimentalna istraživanja, koja nam pokazuju da ima smisla vršiti poređenje između realnih i numeričkih rezultata samo u situaciji gde su broj potrebnih ciklusa i ponašanje zamornih prslina isti. | sr |
dc.description.abstract | Experimental fatigue crack growth analysis of the aircraft structural component subjected to different cycling loading has been presented. The purpose of the experimental test was to evaluates the fatigue behavior of the real aircraft spar, made in aluminum 2024-T3. In-house laboratory fatigue test installation is described in the paper. The spar-test specimen has been manufactured specifically for the cycling damage testing. Test results were obtained with most modern equipment for data acquisition. Applied loads and obtained spar fatigue results are described in detail. Conclusions have been made with reference to the previous work on the duraluminum spar fatigue testing. As it is presented in the previous work with advanced numerical methods for fatigue analysis, in this paper is given an opinion on the same. At the end, possible directions of the further experimental spar fatigue testing is given and shows us that it makes sense to make the comparison between real and numerical results only in situations where cracks behave similarly and the numbers of required cycles are about the same. | en |
dc.publisher | Univerzitet u Beogradu - Mašinski fakultet, Beograd | |
dc.rights | openAccess | |
dc.rights.uri | https://creativecommons.org/licenses/by/4.0/ | |
dc.source | FME Transactions | |
dc.subject | wing spar | en |
dc.subject | test installation | en |
dc.subject | fatigue testing | en |
dc.subject | crack | en |
dc.subject | alluminum alloy 2024-T3 | en |
dc.title | Eksperimentalno određivanje zamornogh veka duraluminijumske ramenjače krila | sr |
dc.title | Aircraft duraluminum wing spar fatigue testing | en |
dc.type | article | |
dc.rights.license | BY | |
dc.citation.epage | 536 | |
dc.citation.issue | 4 | |
dc.citation.other | 45(4): 531-536 | |
dc.citation.rank | M24 | |
dc.citation.spage | 531 | |
dc.citation.volume | 45 | |
dc.identifier.doi | 10.5937/fmet1704531P | |
dc.identifier.fulltext | http://machinery.mas.bg.ac.rs/bitstream/id/1325/2594.pdf | |
dc.identifier.scopus | 2-s2.0-85021191598 | |
dc.identifier.wos | 000408083800011 | |
dc.type.version | publishedVersion |