Optimal design of grid-stiffened panels and shells with variable curvature

Composite Structures

Volumn 52, Issue 2, 2001, Pages 173-180

  Ambur, Damodar R ^a   Jaunky, Navin ^b  

^a NASA LANGLEY RESEARCH CENTER   (United States)

^b Eagle Aeronautics   (United States)

Author keywords

Curvature; Discrete optimizer; Grid stiffened panels and shells

Indexed keywords

ANISOTROPY; BOUNDARY CONDITIONS; BUCKLING; SHEAR STRESS; SHELLS (STRUCTURES); STIFFNESS; STRESS ANALYSIS; STRUCTURAL DESIGN; STRUCTURAL PANELS;

GRID STIFFENED PANELS; RAYLEIGH-RITZ METHOD; STIFFENERS;

COMPOSITE STRUCTURES;

AIRCRAFT; DESIGN; LAMINATE; STIFFNESS; THEORY;

EID: 0035340682     PISSN: 02638223     EISSN: None     Source Type: Journal    
DOI: 10.1016/S0263-8223(00)00165-3     Document Type: Article

References (13)

1. Optimal design of grid-stiffened composite panels using global and local buckling analyses
2. Continuous filament wound composite concepts for aircraft fuselage structures
3. Structural analysis and optimum design of geodesically stiffened composite panels
4. Optimal design of geodesically stiffened composite cylindrical shell
5. Recent enhancements to PANDA2
6. Design of a blade stiffened composite panel by genetic algorithm
7. Design of stiffened panels by genetic algorithm and response surface approximations
8. Damage tolerance and failure analysis of a geodesically stiffened structure loaded in axial compression
9. Buckling analysis of anisotropic curved panels and shells with variable curvature
10. An improved first approximation theory for thin shells
11. An improved smeared theory for buckling analysis of grid-stiffened composite panels
12. Buckling of arbitrary quadrilateral anisotropic plates
13. Buckling analysis of general triangular anisotropic plates using polynomials