Wing Repair Using an Adhesively Bonded Boron Composite Patch - Design and Verification

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F15%3A%230001903" target="_blank" >RIV/00010669:_____/15:#0001903 - isvavai.cz</a>

Výsledek na webu

<a href="https://www.emeraldinsight.com/doi/abs/10.1108/IJSI-10-2013-0027" target="_blank" >https://www.emeraldinsight.com/doi/abs/10.1108/IJSI-10-2013-0027</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1108/IJSI-10-2013-0027" target="_blank" >10.1108/IJSI-10-2013-0027</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Wing Repair Using an Adhesively Bonded Boron Composite Patch - Design and Verification

Popis výsledku v původním jazyce

Various types of damage or cracking in the structural components of an airframe can occur during the service lifetimes of aging aircraft. These types of damage are commonly repaired with a patch that can be joined to the original structure by different techniques, e.g., riveting and bonding. The purpose of this paper is to describe the repair of a fatigue crack in the metallic wing structure of a jet trainer aircraft using an adhesively bonded boron composite patch. Adhesively bonded composite repair increases the lifetime by at least one order compared with the non-repaired structure. Both surface preparations provide equivalent results. The repair lifetime is significantly influenced by the patch geometry, and the longer patch significantly increasesthe lifetime of the panel. The lifetime of the structure can be increased by ~40-fold if the patch geometry is a rectangle with 1:1.5 proportions of the sides (length in the crack direction/length perpendicular to the crack propagation).

Název v anglickém jazyce

Wing Repair Using an Adhesively Bonded Boron Composite Patch - Design and Verification

Popis výsledku anglicky

Various types of damage or cracking in the structural components of an airframe can occur during the service lifetimes of aging aircraft. These types of damage are commonly repaired with a patch that can be joined to the original structure by different techniques, e.g., riveting and bonding. The purpose of this paper is to describe the repair of a fatigue crack in the metallic wing structure of a jet trainer aircraft using an adhesively bonded boron composite patch. Adhesively bonded composite repair increases the lifetime by at least one order compared with the non-repaired structure. Both surface preparations provide equivalent results. The repair lifetime is significantly influenced by the patch geometry, and the longer patch significantly increasesthe lifetime of the panel. The lifetime of the structure can be increased by ~40-fold if the patch geometry is a rectangle with 1:1.5 proportions of the sides (length in the crack direction/length perpendicular to the crack propagation).

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2015

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název periodika

International Journal of Structural Integrity

ISSN

1757-9864

e-ISSN

1757-9872

Svazek periodika

6

Číslo periodika v rámci svazku

2

Stát vydavatele periodika

GB - Spojené království Velké Británie a Severního Irska

Počet stran výsledku

20

Strana od-do

259-278

Kód UT WoS článku

000214188800008

EID výsledku v databázi Scopus

2-s2.0-84928486813