2015
DOI: 10.1590/1679-78252152
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Quasicomparison Functions and Substructure Synthesis for Framed Structures Stability Analysis

Abstract: The Rayleigh-Ritz-Meirovitch substructure synthesis method (RRMSSM) is extended to buckling analysis in framed structures. The objective is a computational procedure capable of yielding very accurate critical loads through solution of very-low-order eigenvalue problems. In this regard, numerical examples demonstrate that the convergence characteristics of the proposed RRMSSM for stability analysis are superior to those associated with the finite element method.

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Cited by 2 publications
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“…As a matter of fact, work has been carried out also on integrals of beam-column eigenfunctions, where the term ‘beam-column’ implies that the concentration is on structural stability rather than vibrations, 22 and the result of the use of beam-column eigenfunctions and their simplest-expression integrals in the RRMSSM has been also very successful, in buckling analysis of frames. 23 Furthermore, clamped-free beam eigenfunctions have been used also in the modelling of aircraft substructures (fuselage, wings and stabilizers) in a new and efficient theory of dynamics and control of aircraft; computationally efficient because the computer power assumed is one of a personal computer as some aircraft – autopiloted unmanned aerial vehicles – may not carry multiprocessor supercomputers; 9 therefore, in this aircraft-dynamics case, avoidance of numerical integration may be important or economical.…”
Section: Discussionmentioning
confidence: 99%
“…As a matter of fact, work has been carried out also on integrals of beam-column eigenfunctions, where the term ‘beam-column’ implies that the concentration is on structural stability rather than vibrations, 22 and the result of the use of beam-column eigenfunctions and their simplest-expression integrals in the RRMSSM has been also very successful, in buckling analysis of frames. 23 Furthermore, clamped-free beam eigenfunctions have been used also in the modelling of aircraft substructures (fuselage, wings and stabilizers) in a new and efficient theory of dynamics and control of aircraft; computationally efficient because the computer power assumed is one of a personal computer as some aircraft – autopiloted unmanned aerial vehicles – may not carry multiprocessor supercomputers; 9 therefore, in this aircraft-dynamics case, avoidance of numerical integration may be important or economical.…”
Section: Discussionmentioning
confidence: 99%