Linear and Nonlinear Analysis of Shells of Revolution with Asymmetrical Stiffness Properties

In this paper, the authors apply an extension of the direct stiffness method of structural analysis to the linear and nonlinear analysis of shells of revolution under arbitrary static loading with variable thickness properties in the circumferential direction and the meridional direction. The primar...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	Stricklin, James A, DeAndrade, Jose C, Stebbins, Frederick J, Cwiertny, Jr, Anthony J
Format:	Report
Sprache:	eng
Schlagworte:	APOLLO HEAT SHIELD APOLLO SPACECRAFT ASYMMETRY AXIAL DISPLACEMENT BUCKLING BUCKLING PRESSURES CIRCUMFERENTIAL DISPLACEMENT COMPONENT REPORTS CURVATURE DEFLECTION DIRECT STIFFNESS METHOD DISPLACEMENT FOURIER SERIES HARMONICS HEAT SHIELDS HIGH PRESSURE LINEAR ANALYSIS MANNED SPACECRAFT MATRICES(MATHEMATICS) MATRIX DISPLACEMENT METHOD MATRIX METHODS Mechanics MERIDIONAL DISPLACEMENT MERIDIONAL STRESS NODAL DISPLACEMENTS NONLINEAR ANALYSIS NORMAL DISPLACEMENT Numerical Mathematics Protective Equipment SHELLS OF REVOLUTION SHELLS(STRUCTURAL FORMS) SPLASHDOWN STABILITY STABILITY ANALYSIS STATIC LOADS STIFFNESS STIFFNESS MATRIX STRAIN ENERGY STRAIN(MECHANICS) STRESSES STRUCTURAL ANALYSIS Structural Engineering and Building Technology STRUCTURAL MECHANICS SYMPOSIA THICKNESS TRANSVERSE SHEAR Unmanned Spacecraft
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	In this paper, the authors apply an extension of the direct stiffness method of structural analysis to the linear and nonlinear analysis of shells of revolution under arbitrary static loading with variable thickness properties in the circumferential direction and the meridional direction. The primary difference between this research and previously published research is that all the Fourier harmonics in the circumferential direction are now coupled. The thickness variation in the circumferential direction yields an 8N x 8N element stiffness matrix in which N is the number of harmonics. The resulting computer program is used to conduct a linear, nonlinear, and stability analysis of the Apollo aft heat shield. See also AD0703685. Presented at the Conference on Matrix Methods in Structural Mechanics (2nd) held at Wright-Patterson Air Force Base, OH, on 15-17 Oct 1968. Pub. in the Proceedings of the Conference on Matrix Methods in Structural Mechanics (2nd), p1231-1251, 1968. Prepared in cooperation with the NASA Manned Spacecraft Center, Houston, TX. AFFDL-68-150.