Structural optimization of a hat-stiffened panel using response surfaces

Journal of Aircraft

Volumn 39, Issue 1, 2002, Pages 158-166

  Vitali, Roberto ^a,c   Park, Oung ^a,c   Haftka, Raphael T ^a,d   Sankar, Bhavani V ^a,d   Rose, Cheryl A ^b,e  

^a UNIVERSITY OF FLORIDA   (United States)

^b NASA LANGLEY RESEARCH CENTER   (United States)

^c Graduate Research Assistants NIMBUS Lab   (United States)

^d Mechanics and Engineering Science ^*  (United States)

^e AIAA   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

BUCKLING; COMPUTER AIDED DESIGN; COMPUTER SIMULATION; CONSTRAINT THEORY; FINITE ELEMENT METHOD; LAMINATED COMPOSITES; OPTIMIZATION; STIFFNESS; STRESSES;

HAT STIFFENERS; LAMINATED COMPOSITE PANEL; STRESS RESPONSE SURFACES;

AIRCRAFT PARTS AND EQUIPMENT;

EID: 0036183087     PISSN: 00218669     EISSN: None     Source Type: Journal    
DOI: 10.2514/2.2910     Document Type: Article

References (8)

1. Variable complexity design of composite fuselage frames by response surfaces techniques
2. PANDA2-Program for minimum weight design of stiffened composite, locally buckled panels
3. STAGS user manual, version 3.0
4. Structural optimization of a hat-stiffened panel by response surface techniques