Design of fiber metal laminate shear panels for ultra-high capacity aircraft

Aircraft Design

Volumn 4, Issue 2-3, 2001, Pages 99-113

  Wittenberg, T C ^a   Van Baten, T J ^a   De Boer, A ^b  

^a DELFT UNIVERSITY OF TECHNOLOGY   (Netherlands)

^b NATIONAL AEROSPACE LABORATORY NLR   (Netherlands)

Author keywords

[No Author keywords available]

Indexed keywords

AIRCRAFT; BUCKLING; COMPUTER SIMULATION; FAILURE ANALYSIS; FATIGUE OF MATERIALS; FINITE ELEMENT METHOD; FUSELAGES; LAMINATED COMPOSITES; MATHEMATICAL MODELS; STRUCTURAL DESIGN;

FIBER METAL LAMINATES (FML);

STRUCTURAL PANELS;

EID: 0035355533     PISSN: 13698869     EISSN: None     Source Type: Journal    
DOI: 10.1016/S1369-8869(01)00003-9     Document Type: Article

References (11)

1. A summary of diagonal tension. Part I - Methods of analysis
2. A summary of diagonal tension. Part II - Experimental verification
3. Development of titanium structural element allowables for the Boeing SST
4. Postbuckling behavior of composite shear webs