Parametric based design of CFRP honeycomb sandwich cylinder for a spacecraft

Composite Structures

Volumn 65, Issue 1, 2004, Pages 7-12

  Vijayakumar, S ^a  

^a SUPMECA   (France)

Author keywords

[No Author keywords available]

Indexed keywords

ASPECT RATIO; COMPOSITE STRUCTURES; DESIGN; HONEYCOMB STRUCTURES; PARAMETER ESTIMATION; SPACECRAFT; THERMAL EXPANSION;

LUMPED MASSES; OPTIMUM DESIGN; STATIC CONSTRAINTS;

CARBON FIBER REINFORCED PLASTICS;

AEROSPACE TEXTILE; CARBON FIBER; DESIGN; FIBER REINFORCED COMPOSITE;

EID: 2442602428     PISSN: 02638223     EISSN: None     Source Type: Journal    
DOI: 10.1016/S0263-8223(03)00176-4     Document Type: Article

References (9)

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3. Vinson J.R. The behavior of structures composed of composite materials 1986 Martinus Nijhoff USA
4. IDEAS User's manual, SDRC, USA 2000
5. Reese C.D. Bert C.W. Simplified design equations for buckling of axially compressed sandwich cylinders with orthotropic facings and core J. Aircraft 6 6 1999 515-519
6. Sodel W. Simplified equations and solutions for the vibration of orthotropic cylindrical shells J. Sound Vibrat. 87 4 1983 555-566
7. Sharma C.B. Darvizeh M. Darvizeh A. Free vibration response of multilayered orthotropic fluid-filled circular cylindrical shells Compos. Struct. 34 3 1996 349-355
8. Tsai S.W. Hahn H.A.T. Introduction to composite materials 1980 Technomic Publications USA
9. Vijayakumar S, Basha SK, Srinivasan RK. Design details of CFRP honeycomb sandwich cylinder for I-3000 bus. Structures Group, ISRO, 2002