Composite repairs to rib stiffened panels

Composite Structures

Volumn 47, Issue 1-4, 1999, Pages 737-743

  Ting, T ^a   Jones, R ^a   Chiu, W K ^a   Marshall, I H ^a   Greer, J M ^b  

^a MONASH UNIVERSITY   (Australia)

^b UNITED STATES AIR FORCE ACADEMY   (United States)

Author keywords

Bonded repair; Boron patches; Composites; Fracture; Stiffened wing skins

Indexed keywords

BOND STRENGTH (MATERIALS); BORON; CRACK INITIATION; CRACK PROPAGATION; ELASTIC MODULI; EPOXY RESINS; FINITE ELEMENT METHOD; FRACTURE MECHANICS; STRESS CONCENTRATION; STRESS INTENSITY FACTORS;

BONDED REPAIR; BORON PATCHES; STIFFENED WING SKINS;

NONMETALLIC MATRIX COMPOSITES;

REPAIR;

EID: 0033303914     PISSN: 02638223     EISSN: None     Source Type: Journal    
DOI: 10.1016/S0263-8223(00)00046-5     Document Type: Conference Paper

References (9)

1. An application of the inclusion analogy for bonded reinforcements
2. Damage tolerant repair techniques for pressurized aircraft fuselages
3. Structural aspects of the design of an all boron/epoxy reinforcement for the F-111C wing pivot fitting
4. Composite repairs to cracks in thick metallic components