Modal density of thin circular cylinders
Vibration modal response of thin cylindrical shells
SEARCH · Search NASA
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Vibration modal response of thin cylindrical shells
Boundary and continuity conditions for cylindrical shell under nonlinear flexural vibrations, discussing modal approximations for equations of motion
Facility of reaction time to stimulus by signal of differing sense modality
Natural vibration modal analysis as related to space vehicle design criteria
Modal aperture field decomposition for optical detection and radiance estimation on incoherent objects
Temporal pattern perception by human subjects required to integrate information presented in two modalities
Estimated and measured modal densities of sandwich beams and sandwich panels
Objectives and techniques of test program to determine Mariner spacecraft modal characteristics
Dynamic test analysis on modal damping forces of Saturn 5 Apollo vehicle
Modal density estimates for sandwich panels - theory and experiment
Dynamic structural modal synthesis technique
Wave propagation in finite length revolving shells, describing advantages of modal superposition method generated by finite element computer program
Aperture field modal decomposition of optical system in terms of integral equation eigenfunctions during detection and estimation of incoherent objects
Modal analysis computer program package for finding frequencies and mode shapes of any linear discrete system governed by generalized eigenvalue equation
Expressions and graphs for estimating average modal densities for various structural elements of engineering importance including beams, rods, circular plates, and conical shells
The derivation of minimum-dimension sets of discrete-coordinate and hybrid-coordinate equations of motion of a system consisting of an arbitrary number of hinge-connected rigid bodies assembled in tree topology is presented. These equations are useful for the simulation of dynamical systems that can be idealized as tree-like arrangements of substructures, with each substructure consisting of either a rigid body or a collection of elastically interconnected rigid bodies restricted to small relative rotations at each connection. Thus, some of the substructures represent elastic bodies subjected to small strains or local deformations, but possibly large gross deformations, in the hybrid formulation, distributed coordinates referred to herein as large-deformation modal coordinates, are used for the deformations of these substructures. The equations are in a form suitable for incorporation into one or more computer programs to be used as multipurpose tools in the simulation of spacecraft and other complex electromechanical systems.
Various procedures for analytically coupling two or more substructures to obtain modal data for assembly, using data obtained from mode surveys of the individual components are discussed. Particular attention was paid to the applicability of the techniques investigated to the space shuttle, with the possible replacement of full scale mode surveys of the shuttle assembly by component mode surveys along with analytical coupling. The synthesis procedures formulated in this report can all handle redundant connections, although the presence of redundancies does add complication to one of the techniques. All of the procedures use the test data directly, without going through an intermediate analytical model, and no analytical stiffness data is required to supplement the mode survey data. The coupling precedures were initially verified and evaluated by applying them to analytical check problems.
This study consisted of four parallel efforts: (1) modal analyses of elastic continua for Liapunov stability analysis of flexible spacecraft; (2) development of general purpose simulation equations for arbitrary spacecraft; (3) evaluation of alternative mathematical models for elastic components of spacecraft; and (4) examination of the influence of vehicle flexibility on spacecraft attitude control system performance. A complete record is given of achievements under tasks (1) and (3), in the form of technical appendices, and a summary description of progress under tasks two and four.