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  • Other Sources  (1,064)
  • STRUCTURAL MECHANICS  (546)
  • SPACE VEHICLES  (518)
  • Analytical Chemistry and Spectroscopy
  • Physics
  • 1980-1984  (214)
  • 1965-1969  (850)
  • 1980  (214)
  • 1968  (850)
Collection
Source
Keywords
Years
  • 1980-1984  (214)
  • 1965-1969  (850)
Year
  • 1
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    Development of gravity-gradient dampers (1968)
    In:  CASI
    Details
    Publication Date: 2005-11-17
    Description: Suspension and energy dissipation couplings in satellity gravity gradient stabilization system
    Keywords: SPACE VEHICLES
    Type: JPL PROC. OF THE 3RD AEROSPACE MECH. SYMP. 1 OCT. 1968; P 211-218
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  • 2
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    Soil mechanics surface sampler (1968)
    In:  CASI
    Details
    Publication Date: 2005-11-13
    Description: Soil mechanics surface sampler and analysis of samples from Surveyor 7 Tycho landing site
    Keywords: SPACE VEHICLES
    Type: SURVEYOR 7 MISSION REPT. PT. 2 - SCI. RESULTS 15 MAR. 1968; P 135-185
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  • 3
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    Television observations from Surveyor 7 (1968)
    In:  CASI
    Details
    Publication Date: 2005-11-13
    Description: Topography of Tycho lunar landing site from Surveyor 7 television pictures
    Keywords: SPACE VEHICLES
    Type: SURVEYOR 7 MISSION REPT. PT. 2 - SCI. RESULTS 15 MAR. 1968; P 9-76
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  • 4
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    Planetary-interplanetary program (1968)
    In:  CASI
    Details
    Publication Date: 2005-11-13
    Description: Mariner 4, Mariner Venus 67, and Mariner Mars interplanetary spacecraft
    Keywords: SPACE VEHICLES
    Type: SPACE PROGRAMS SUM. NO. 37-49, VOL. 1 FOR THE PERIOD NOV. 1 TO DEC. 31, 1967. FLIGHT PROJ. 31 JAN. 1968; P 1-30
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  • 5
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    Random-vibration response data for orbiting geophysical observatory - Flight, acoustic, and vibration test (1968)
    In:  CASI
    Details
    Publication Date: 2005-11-13
    Description: Random vibration response data for orbiting geophysical observatory - comparative analysis of flight, acoustic, and vibration tests
    Keywords: STRUCTURAL MECHANICS
    Type: NRL THE SHOCK AND VIBRATION BULL. JAN. 1968; P 21-45
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  • 6
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    Lunar program (1968)
    In:  CASI
    Details
    Publication Date: 2005-11-13
    Description: Surveyor lunar program
    Keywords: SPACE VEHICLES
    Type: SPACE PROGRAMS SUM. NO. 37-49, VOL. 1 FOR THE PERIOD NOV. 1 TO DEC. 31, 1967. FLIGHT PROJ. 31 JAN. 1968; P 31-64
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  • 7
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    Reduction of control system design effort (1968)
    In:  CASI
    Details
    Publication Date: 2005-11-13
    Description: Reliable control systems with satisfactory dynamic response for launch vehicles
    Keywords: SPACE VEHICLES
    Type: ASTRODYN., GUIDANCE AND CONTROL REV. NO. 1 21 FEB. 1968; P 35-38
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  • 8
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    Techniques developed to determine aerodynamic coefficients for Apollo applications program vehicles in an orbital environment (1968)
    In:  CASI
    Details
    Publication Date: 2006-06-08
    Description: Computer programs to determine aerodynamic coefficients for Apollo Applications Program vehicles in orbital environment
    Keywords: SPACE VEHICLES
    Type: RES. ACHIEVEMENTS REV., VOL. 3 1968; P 51-60
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  • 9
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    Flow characteristics of orifices for venting launch vehicle compartments (1968)
    In:  CASI
    Details
    Publication Date: 2006-06-08
    Description: Flow characteristics of orifices for venting launch vehicle compartments
    Keywords: SPACE VEHICLES
    Type: RES. ACHIEVEMENTS REV., VOL. 3 1968; P 25-34
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  • 10
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    Rockets at large angles of attack (1968)
    In:  CASI
    Details
    Publication Date: 2006-06-08
    Description: Prediction of aerodynamic characteristics for rockets at large angles of attack
    Keywords: SPACE VEHICLES
    Type: RES. ACHIEVEMENTS REV., VOL. 3 1968; P 1-10
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  • 11
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    Development and verification of the vibration test requirements for the Apollo command and service modules (1968)
    In:  CASI
    Details
    Publication Date: 2006-02-07
    Description: Development and verification of vibration test requirements for Apollo command and service modules
    Keywords: STRUCTURAL MECHANICS
    Type: NRL THE SHOCK AND VIBRATION BULL., NO. 37, PT. 5 JAN. 1968; P 89-103
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  • 12
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    Development of acoustic test conditions for Apollo lunar module flight certification (1968)
    In:  CASI
    Details
    Publication Date: 2006-02-05
    Description: Acoustic test conditions to verify structural and component integrity of Apollo lunar module
    Keywords: STRUCTURAL MECHANICS
    Type: NRL THE SHOCK AND VIBRATION BULL., NO. 37, PT. 5 JAN. 1968; P 139-152
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  • 13
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    Real-time combined acoustic-vacuum testing of spacecraft (1968)
    In:  CASI
    Details
    Publication Date: 2006-02-07
    Description: Acoustic qualification testing of aerodynamic fins used on S-1C stage of Saturn 5 vehicle
    Keywords: STRUCTURAL MECHANICS
    Type: NRL THE SHOCK AND VIBRATION BULL., NO. 37, PT. 5 JAN. 1968; P 175-182
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  • 14
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    Saturn S-2, S-4B, and instrument unit subassembly and assembly vibration and acoustic evaluation programs (1968)
    In:  CASI
    Details
    Publication Date: 2006-02-07
    Description: Saturn S-2, S-4B, and instrument unit subassembly and assembly vibration and acoustic evaluation programs
    Keywords: STRUCTURAL MECHANICS
    Type: NRL THE SHOCK AND VIBRATION BULL., NO. 37, PT. 5 JAN. 1968; P 117-137
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  • 15
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    Nonlinear vibrations of beams with various boundary conditions. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Amplitude frequency relations of nonlinear vibrations in uniform beams with various boundary conditions using perturbation method
    Keywords: STRUCTURAL MECHANICS
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  • 16
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    Effects of 450 deg and 600 deg F exposures on the mechanical properties of polyimide/glass- fiber honeycomb sandwiches and laminated beams. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Polymide resin/glass fiber sandwich panels studied for high temperature effects on mechanical properties for application to SST
    Keywords: STRUCTURAL MECHANICS
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  • 17
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    Earth-orbital lifetime and satellite decay. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Orbital behavior of large irregular shaped spacecraft with life and delay prediction from laboratory tests and experiments
    Keywords: SPACE VEHICLES
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  • 18
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    Simulated micrometeoroid degradation of thermal control coatings. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Simulated micrometeoroid bombardment of white thermal control coating causing changes in optical properties
    Keywords: STRUCTURAL MECHANICS
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  • 19
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    A simplified procedure for determining the perforation limits for thin plates. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Thin plate ballistic limit for perforation by cylindrical projectiles, using computational procedures and graphs
    Keywords: STRUCTURAL MECHANICS
    Type: ; IVERSITET DRUZHBY NA
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  • 20
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    Effect of edge restraint coupling on buckling of ring-supported cylinders. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Edge restraint coupling effect on buckling mode of ring stiffened shells of revolution
    Keywords: STRUCTURAL MECHANICS
    Type: ; IVERSITET DRUZHBY NA
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  • 21
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    Launch probability models for a single space vehicle. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Launch probability models to determine tradeoffs for single space vehicle
    Keywords: SPACE VEHICLES
    Type: ; ADEMIE DES SCIENCES
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  • 22
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    Vibration analysis of stiffened cylinders including inter-ring motion. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Vibrational characteristics of ring stiffened cylindrical shells including inter-ring motion, comparing results with energy methods and orthotropic approach
    Keywords: STRUCTURAL MECHANICS
    Type: ; YAL SOCIETY (
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  • 23
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    Elastic buckling of heated doubly curved thin shells. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Elastic buckling and postbuckling behavior of thin doubly curved shell panels subject to nonuniform heating, noting load vs deflection
    Keywords: STRUCTURAL MECHANICS
    Type: ; ECTRON (
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  • 24
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    Nimbus - A progress report. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Flight accomplishments of Nimbus satellites and progress in meteorological spacecraft observatory systems since program initiation
    Keywords: SPACE VEHICLES
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  • 25
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    Transmission characteristics of conical and cylindrical shells under lateral excitation. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Steady state frequency response of conical and cylindrical shells under lateral excitation
    Keywords: STRUCTURAL MECHANICS
    Type: ; YAL SOCIETY (
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  • 26
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    Elastic displacements for various edge-cracked plate specimens. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Elastic displacements for edge cracked plate specimens used as crack extension indicator in plane strain fracture toughness measurements
    Keywords: STRUCTURAL MECHANICS
    Type: ; UGREVUE(
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  • 27
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    Resonant perturbations of existing satellites. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Geopotential resonant orbital perturbations of existing satellites, noting high inclination role
    Keywords: SPACE VEHICLES
    Type: ; ACE(
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  • 28
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    Behavior of elastic networks of various degrees of orientation in the kinetic theory of fracture. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Kinetic theory of fracture initiation, discussing changes in relative orientation distribution of network chains
    Keywords: STRUCTURAL MECHANICS
    Type: ; VIGATION (
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  • 29
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    Why space stations? (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Space station design requirements, Apollo applications program and various experimental programs
    Keywords: SPACE VEHICLES
    Type: ; ADEMIE DES SCIENCES
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  • 30
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    Landing dynamics studies of the Surveyor spacecraft. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Surveyor spacecraft landing dynamics, using mathematical model to predict touchdown conditions for spacecraft pretouchdown motion and orientation
    Keywords: SPACE VEHICLES
    Type: ; ADEMIE DES SCIENCES
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  • 31
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    Structural research and development for cryogenic upper stages. II. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Research and development in structural and thermal analysis, materials and fabrication techniques for spacecraft upper stages utilizing cryogenic propellants
    Keywords: SPACE VEHICLES
    Type: ; YAL SOCIETY (
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  • 32
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    Measurements of mixed-mode crack surface displacements and comparison with theory (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The problem of a finite-width tension specimen containing a crack oriented at various angles to the load axis is attacked from experimental and theoretical viewpoints. Displacements of an electro-machined slot, 12.5 mm long and oriented at angles of 0, 15, 30, 45, 60, and 75 deg, are measured using a laser-based in-plane measuring technique. Various width specimens, ranging from a crack-length/width ratio of 0.167 to 0.794, are tested. A boundary-integral equation method is extended to deal with the presence of a sharp crack. Agreement between the two approaches is generally good except near the tips of the cracks.
    Keywords: STRUCTURAL MECHANICS
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  • 33
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    Green's function for a crack emanating from a circular hole in an infinite sheet (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Stress-intensity factors, K/I/ and K/II/, are obtained for a point loaded crack emanating from a circular hole in an infinite plate. A series approach and the Muskhelishvili formulation in the two-dimensional theory of elasticity are used to derive the solution. The applicability of the solution is demonstrated by using it as a Green's function to obtain K/I/ and K/II/ and the case of (1) biaxial tension of an infinite plate and (2) bending of a wide strip.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal of Fracture; 16; Aug. 198
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  • 34
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    Response of a panel to a supersonic turbulent boundary layer - Studies on a theoretical model (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A study of the response of a clamped panel to a supersonic turbulent boundary layer, based on a recently developed theoretical model, is presented. It is demonstrated that the model incorporates the effect of coupling between the panel motion and the flow of the surrounding fluid. Further, a Ritz-Galerkin method is used to obtain approximate solutions for the statistics of the panel response to the turbulence. The numerical results are compared with previous experimental data and the theoretical model is assessed.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Sound and Vibration; 71; July 22
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  • 35
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    Vibration and buckling of rectangular plates under in-plane hydrostatic loading (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Numerical solutions are presented for the fundamental natural frequency and mode shape of a rectangular plate loaded by in-plane hydrostatic forces for a wide variety of aspect ratios, boundary conditions, and load magnitudes. All six possible combinations of simply supported and clamped edges are considered. The limiting conditions of unloaded vibration and buckling are discussed in detail, with emphasis on the preferred mode shape. Design curves and approximate formulae are presented which provide a simple means of determining the fundamental frequency parameter.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Sound and Vibration; 70; June 22
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  • 36
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    An assessment of buffer strips for improving damage tolerance of composite laminates (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Graphite/epoxy panels with buffer strips were tested in tension to measure their residual strength with crack-like damage. Panels were made with (45/0/-45/90)2S and (45/0/-45/0)2S layups. The buffer strips were parallel to the loading direction. They were made by replacing narrow strips of the 0 deg graphite plies with strips of either 0 deg S-Glass/epoxy or Kevlar-90/epoxy on either a one-for-one or a two-for-one basis. In a third case, 0 deg graphite/epoxy was used as the buffer material and thin, perforated Mylar strips were placed between the 0 deg plies and the cross-plies to weaken the interfaces and thus to isolate the 0 deg plies. Some panels were made with buffer strips of different width and spacings. The buffer strips arrested the cracks and increased the residual strengths significantly over those of plain laminates without buffer strips. A shear-lag type stress analysis correctly predicted the effects of layup, buffer material, buffer strip width and spacing, and the number of plies of buffer material
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Composite Materials Supplement; 14; 1, 19; 1980
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  • 37
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    Development and evaluation of two non-linear shell elements (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Two plate and shell displacement elements are developed for use in large deflection non-linear analysis. The elements are of the 'stability' type, in which non-linear strains are included, with their values optimized by added higher order membrane functions and special types of elemental level constraints. The paper summarizes formulation and computational procedures, and discusses numerical results in detail. Conclusions are given regarding the effectiveness of the elements for solving both linear and non-linear shell analysis problems.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal for Numerical Methods in Engineering; 16; Oct. 198
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  • 38
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    Mode I fracture behavior of nonlinear materials (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A finite element analysis is presented for the Mode I fracture behavior of cracked plates (stationary crack) made of different nonlinear materials (elastoplastic or elastic locking). The assumed stress-strain behavior of the nonlinear materials was piecewise linear. For each given 'stationary' crack size, the corresponding critical remote tensile stress was calculated based on the maximum crack-tip stress failure criterion. It was found that in the log-log plots of the critical remote stress versus critical crack length, the fracture data of the piecewise linear materials obey a 'stepwise-linear-inverse-square-root' fracture law. It is also shown how the fracture data of the piecewise linear materials can be fitted by proper piecewise graphical shifting of the classical 'inverse-square-root' fracture curve for the linearly elastic materials.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal of Fracture; 16; June 198
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  • 39
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    Energy minimization versus pseudo force technique for nonlinear structural analysis (1980)
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    Publication Date: 2011-08-17
    Description: The effectiveness of using minimization techniques for the solution of nonlinear structural analysis problems is discussed and demonstrated by comparison with the conventional pseudo force technique. The comparison involves nonlinear problems with a relatively few degrees of freedom. A survey of the state-of-the-art of algorithms for unconstrained minimization reveals that extension of the technique to large scale nonlinear systems is possible.
    Keywords: STRUCTURAL MECHANICS
    Type: Computers and Structures; 11; May 1980
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  • 40
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    Recent developments in the design, testing and impact-damage tolerance of stiffened composite panels (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The structural technology of laminated filamentary-composite stiffened-panel structures under combined in-plane and lateral loadings is discussed. Emphasis is on analyzing the behavior of the structures under load, determining appropriate structural proportions for weight efficient configurations, and effects of impact damage and geometric imperfections on structural performance. Experimental data on buckling of panels under in-plane compression validate the analysis and sizing methods, and illustrate structural performance and efficiency obtained from representative structures. It is shown that the strength of panels under in-plane compression can be degraded by low-velocity impact damage, and data are presented which indicate that the matrix is a significant factor influencing tolerance to impact damage.
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  • 41
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    Automatic checkout and control (1968)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Automatic checkout and control of launch vehicles during prelaunch phase, and utilization of techniques in electric power industry
    Keywords: SPACE VEHICLES
    Type: SELECTED TECHNOL. FOR THE ELEC. POWER IND. 1968; P 157-171
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  • 42
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    Thermophysics research (1968)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Thermal environment control for spacecraft
    Keywords: SPACE VEHICLES
    Type: PROC. OF THE THIRD SOUTHEASTERN SEMINAR ON THERMAL SCI. 8 MAY 1968; P 143-191
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  • 43
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    Lox prevalve to prevent Pogo effect on Saturn 5. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: LOX prevalve accumulator system with He pressurant for prevention of Pogo effect on Saturn 5
    Keywords: SPACE VEHICLES
    Type: SPACE(AERONAUTICS, VOL. 50, P. 72-74.
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  • 44
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    Dynamic stability of symmetric spinning missiles. (1968)
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    Publication Date: 2011-08-12
    Description: High drag planetary entry vehicles dynamic stability prediction accounting for gravitational effects in terminal flight at small roll rates
    Keywords: SPACE VEHICLES
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  • 45
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    Strength calculations for sheet-metal parts with cracks. (1968)
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    Publication Date: 2011-08-12
    Description: Strength of sheet metal parts containing cracks studied by simulating fail safe design
    Keywords: STRUCTURAL MECHANICS
    Type: ; ADEMIE DES SCIENCES
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  • 46
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    Effects of aerodynamic torque on an asymmetric, gravity-stabilized satellite. (1968)
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    Publication Date: 2011-08-12
    Description: Aerodynamic and gravitational torque effects on asymmetric gravity stabilized satellite
    Keywords: SPACE VEHICLES
    Type: ; ACE(
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  • 47
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    Biosatellite II operations. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Biosatellite 2 operations, discussing orbiting by two stage delta launch vehicle, battery powering and STADAN planned communications
    Keywords: SPACE VEHICLES
    Type: ; URNAL OF PHYSICS, PA
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  • 48
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    High-frequency plate damping due to gas pumping in riveted joints. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: HF plate vibration damping due to gas pumping in riveted joints, considering pressure dependence of viscosity
    Keywords: STRUCTURAL MECHANICS
    Type: ; UGREVUE(
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  • 49
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    The Biosatellite II mission. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Preparational, operational and recovery stages of Biosatellite 2 mission
    Keywords: SPACE VEHICLES
    Type: ; URNAL OF PHYSICS, PA
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  • 50
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    Biosatellite II experiment environment. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Automated laboratory in Biosatellite 2 reentry vehicle, discussing experiments
    Keywords: SPACE VEHICLES
    Type: ; URNAL OF PHYSICS, PA
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  • 51
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    A nonlinear boundary layer for shells of revolution. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Nonlinear boundary layer for shells of revolution, deriving nonlinear differential equations for infinitesimal strains and small rotation
    Keywords: STRUCTURAL MECHANICS
    Type: ; URNAL OF PHYSICS, PA
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  • 52
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    Propagation of plastic strain pulses in cylindrical lead bars. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Plastic strain pulse propagation in cylindrical lead bars, discussing stress-strain-time deformation
    Keywords: STRUCTURAL MECHANICS
    Type: ; ACE(
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  • 53
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    Time-dependent mechanical strength of oriented media. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Time dependent theory of mechanical strength of homogeneous and partially oriented and stressed media based on microscopic molecular structure
    Keywords: STRUCTURAL MECHANICS
    Type: ; ACE(
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  • 54
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    Roll resonance for a gravity-gradient satellite. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Equation providing nodal angle for largest roll libration with twice orbital frequency derived for gravity gradient satellite
    Keywords: SPACE VEHICLES
    Type: ; URNAL OF PHYSICS, PA
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  • 55
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    Entry maneuvers for large lateral and small longitudinal range. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Hypersonic entry vehicle aerodynamic maneuvers for generating large lateral and small longitudinal range
    Keywords: SPACE VEHICLES
    Type: ; URNAL OF PHYSICS, PA
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  • 56
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    Modification of elastic properties in structural analysis by force method. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Structural analysis modification by force method accounting for elastic property changes of some elements
    Keywords: STRUCTURAL MECHANICS
    Type: ; ADEMIE DES SCIENCES
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  • 57
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    Explicit expressions for triangular torus element stiffness matrix. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Explicit expressions for stiffness matrix of triangular torus elements associated with linear displacement fields and generalized Hookian material
    Keywords: STRUCTURAL MECHANICS
    Type: ; ADEMIE DES SCIENCES
    Format: text
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  • 58
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    Four-pole parameters for impedance analyses of conical and cylindrical shells under axial excitations. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Four pole parameters of truncated thin conical shell under axial excitations obtained by applying membrane shell theory
    Keywords: STRUCTURAL MECHANICS
    Type: ; L AVIV AND HAIFA, IS
    Format: text
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  • 59
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    Buckling of ogive shell under external pressure. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Approximate buckling load for thin ogive shell of revolution under uniform external pressure using differential equations
    Keywords: STRUCTURAL MECHANICS
    Type: ; L AVIV AND HAIFA, IS
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  • 60
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    Buckling of doubly curved shallow thin shells. (1968)
    In:  Other Sources
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    Publication Date: 2011-08-12
    Description: Doubly curved shallow thin shells buckling under edge loading, discussing curvatures role and shell equation
    Keywords: STRUCTURAL MECHANICS
    Type: ; ACE(
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  • 61
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    Application of a method of estimating high- temperature low-cycle fatigue behavior of materials. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Metal alloys high temperature low cycle strain fatigue resistance in creep range estimated from tensile and stress rupture data
    Keywords: STRUCTURAL MECHANICS
    Type: ; YAL SOCIETY (
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  • 62
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    Saturn launch vehicles astrionics system. (1968)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Saturn launch vehicles astrionics system, reviewing navigation, guidance, control and communication functions of electronic instrument on S-4B stage
    Keywords: SPACE VEHICLES
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  • 63
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    Thermally induced response of flexible structures - A method for analysis (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The phenomenon of a thermally induced spacecraft instability became apparent during the flight of the OGO-IV spacecraft in the late 1960s. The paper presents a generalized approach to the problem of obtaining a computationally practical simulation model for a thermally driven structure. The formulation is such that it can be utilized in a stand-along manner or be meshed into a general multibody simulation model such as that reported by Bodley et al. (1978). As presented, the formulation is restricted to the dynamic range for which linearized radiation is a valid assumption.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Guidance and Control; 3; Jan
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  • 64
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    Stress-intensity factors for internal surface cracks in cylindrical pressure vessels (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The paper presents stress-intensity factors for a wide range of semi-elliptical surface cracks on the inside of pressurized cylinders. The ratio of crack depth to crack length ranged from 0.2 to 1; the ratio of crack depth to wall thickness ranged from 0.2 to 0.8; and the ratio of wall thickness to vessel radius was 0.1 to to 0.25. The stress-intensity factors were calculated by a three-dimensional finite-element method using singularity elements along the crack front and linear-strain elements elsewhere. An equation for the stress-intensity factors was obtained which applies over a wide range of configuration parameters and was within about 5 percent of the present results. A comparison was also made between the results and other analyses of internal surface cracks in cylinders. The results from a boundary-integral equation method were in agreement and those from another finite-element method were in fair agreement (+ or - 8 percent) with the results.
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  • 65
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    A wide range stress intensity factor expression for the C-shaped specimen (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Testing and Evaluation; 8; Nov. 198
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  • 66
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    A consistent set of trial functions for conical shells (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A consistent approach is developed for the determination of trial functions for a class of shells of revolution. The trial functions satisfy the in-plane and out-of-plane boundary conditions at the shell ends and include the effects of tangential inertia. The resulting expressions converge rapidly for the problem of linear free vibration
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Sound and Vibration; 73; Nov. 8
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  • 67
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    Improvements to the NASAP code (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The FORTRAN code, NASAP was modified and improved for the capability of transforming the CAD-generated NASTRAN input data for DESAP II and/or DESAP I. The latter programs were developed for structural optimization.
    Keywords: STRUCTURAL MECHANICS
    Type: Alabama Univ. Res. Rept.: The 1980 NASA(ASEE Summer Fac. Fellowship Program; 76 p
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  • 68
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    Buckling of axially compressed conical shells (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The buckling of a truncated elastic conical shell subjected to an axial compression is a classical problem in shell structures. The paper reinvestigates the buckling of an axially compressed truncated conical shell with rigid bulkheads. Two improvements are achieved. First, the condition that the total horizontal displacement must vanish due to rigid bulkhead and axisymmetry is treated as a constraint. This constraint is incorporated into the system through the use of the Lagrange multiplier; then the variational method is used to derive a complete set of boundary conditions for conical shells. Second, the stability is evaluated in the deformed state using the asymptotic solutions of the pair of Donnell-type equations for axisymmetric configuration. The results indicate that the buckling strength of conical shells depends mainly on the condition of the smaller end. In addition to the vertex angle, the distance ratio plays, at least, an equally important role.
    Keywords: STRUCTURAL MECHANICS
    Type: American Society of Civil Engineers; Journal
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  • 69
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    Maintenance of NASTRAN (R) as a state-of-the-art computer program (1980)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The maintenance requirements for a large, general purpose, finite element computer program are presented. The program is maintained as state-of-the-art on three computer systems (IBM, CDC, and UNIVAC) with respect to both finite element and computer technology. There are four primary areas involved in the maintenance effort: (1) error correction; (2) incorporation of advances in technology; (3) documentation; and (4) new level generation. The complexity of the maintenance effort is compounded by the sizes of the program (400,000 lines of code) and the documentation (7000 pages divided into seven manuals).
    Keywords: STRUCTURAL MECHANICS
    Type: AGARD The Use of Computers as a Design Tool; 12 p
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  • 70
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    Surveyor spacecraft (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: EMI requirements developed for Surveyor spacecraft
    Keywords: SPACE VEHICLES
    Type: JPL PROC. OF THE SPACECRAFT ELECTROMAGNETIC INTERFERENCE WORKSHOP 15 DEC. 1968; P 55-72
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  • 71
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    Comparison of finite element analysis of a piping tee using NASTRAN and CORTES/SA (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A comparison of finite element analyses of a piping tee was made using NASTRAN and CORTES/SA, a modified version of SAP3 having a special purpose input processor for generating geometries for a wide variety of tee joints. Four finite element models were subjected in force, moment, and pressure loadings. Flexibility factors and principal stresses were computed for each model and compared with results obtained experimentally by Combustion Engineering, Inc. Results from the NASTRAN analyses were in good agreement with experimental results for all loadings except internal pressure. The CORTES/SA analyses gave good results for the internal pressure loading, but poorer results for out of plane bending moments or forces resulting in out of plane bending. Two of the basic load cases in CORTES/SA were found to contain errors that could not be easily corrected. COST COMPARison of NASTRAN and CORTES/SA showed NASTRAN to be less expensive to two than CORTES/SA for identical meshes.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 224-242
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  • 72
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    On the application of nonlinear load elements to thermal analyses using the NASTRAN thermal analyzer (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The nonlinear load elements in thermal analysis are used to simulate an undocumented nonlinear thermal boundary condition. The treatment of the nonlinearity arising from the temperature-dependent convective film coefficients is shown in detail. As an illustration, emphasis is placed on the modeling techniques and their interrelationships with the solution accuracy as affected by a specific integration algorithm of the transient thermal analysis used in the NASTRAN Thermal Analyzer. Briefly shown is the underlying theory on which the maneuvering of terms pertinent to the modeling depends. This demonstration provides some insight into the intricacies of the method that would be general to all applications. A recommendation is also made to modify a nonlinear load element that will enhance the solution capability and broaden the scope of application.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 121-139
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  • 73
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    Solution of enforced boundary motion in direct transient and harmonic problems (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The current versions of NASTRAN, i.e., NASA, MSC, and MAC support nonzero boundary displacements only in the static analysis. Forcing functions in the dynamic analysis formats allow only forces and pressures to exercise the mathematical model. A DMAP alter sequence to circumvent this limitation is described. For the direct harmonic problem, a simple change to module FRRD is incorporated to effect a more efficient use of the code.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 96-120
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  • 74
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    Solution sensitivity and accuracy study of NASTRAN for large dynamic problems involving structural damping (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Large dynamic problems involving NASTRAN SOLUTION 8 (i.e., the steady state dynamic response option wherein all response quantities vary as e sub i omega t, where omega is the driving frequency and t is time) are considered. Using a submerged steel plate with a viscoelastic layer layer as the bench mark sample, the solution sensitivity and solution accuracy are checked. The solution sensitivity is examined by running the same finite element model on different computers, different versions of NASTRAN, and different precision levels. The solution accuracy is evaluated for these same runs by comparing the NASTRAN results with the exact solution of the same problem.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 49-62
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  • 75
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    Iterative methods based upon residual averaging (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Iterative methods for solving boundary value problems for systems of nonlinear partial differential equations are discussed. The methods involve subtracting an average of residuals from one approximation in order to arrive at a subsequent approximation. Two abstract methods in Hilbert space are given and application of these methods to quasilinear systems to give numerical schemes for such problems is demonstrated. Potential theoretic matters related to the iteration schemes are discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 91-96
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  • 76
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    New capacities and modifications for NASTRAN level 17.5 at DTNSRDC (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Since 1970 DTNSRDC has been modifying NASTRAN to suite various Navy requirements. These modifications include capabilities as well as user conveniences and error corrections. The new features added to NASTRAN Level 17.5 are described. The subject areas of the additions include magnetostatics, piezoelectricity, fluid structure interactions, isoparametric finite elements, and shock design for shipboard equipment.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 1-13
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  • 77
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    Solutions of contact problems by the assumed stress hybrid model (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A method was developed for contact problems which may be either frictional or frictionless and may involve extensive sliding between deformable bodies. It was based on an assumed stress hybrid approach and on an incremental variational principle for which the Euler's equations of the functional include the equilibrium and compatibility conditions at the contact surface. The tractions at an assumed contact surface were introduced as Lagrangian multipliers in the formulation. It was concluded from the results of several example solutions that the extensive sliding contact between deformable bodies can be solved by the present method.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 211-224
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  • 78
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    Finite element analysis of hyperelastic structures (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The use of the penalty function, to account for near incompressibility is discussed and compared to that of Lagrange multiplier. A scheme to use Lagrange multiplier, without having to treat it as unknown, is also presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 197-209
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  • 79
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    Study of solution procedures for nonlinear structural equations (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A method for the redution of the cost of solution of large nonlinear structural equations was developed. Verification was made using the MARC-STRUC structure finite element program with test cases involving single and multiple degrees of freedom for static geometric nonlinearities. The method developed was designed to exist within the envelope of accuracy and convergence characteristic of the particular finite element methodology used.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 129-139
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  • 80
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    Thermal stress response of General Purpose Heat Source (GPHS) aeroshell material (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A thermal stress test was conducted to determine the ability of the GPHS aeroshell 3 D FWPF material to maintain physical integrity when exposed to a severe heat flux such as would occur from prompt reentry of GPHS modules. The test was performed in the Giant Planetary Facility at NASA's Ames Research Center. Good agreement was obtained between the theoretical and experimental results for both temperature and strain time histories. No physical damage was observed in the test specimen. These results provide initial corroboration both of the analysis techniques and that the GPHS reentry member will survive the reentry thermal stress levels expected.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Johnson Space Center The 11th Space Simulation Conf.; p 378-389
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  • 81
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    Finite circular plate on elastic foundation centrally loaded by rigid spherical indenter (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The analytical solution of a finite circular plate on an elastic foundation centrally loaded by the rigid indenter is discussed. The procedure to use NASTRAN as a subroutine to iteratively converge to this solution numerically is described.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 173-190
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    A NASTRAN investigation of simulated projectile damage effects on a UH-1B tail boom model (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A NASTRAN model of a UH-1B tail boom that had been designed for another project was used to investigate the effect on structural integrity of simulated projectile damage. Elements representing skin, and sections of stringers, longerons and bulkheads were systematically deleted to represent projectile damage. The structure was loaded in a manner to represent the flight loads that would be imposed on the tail boom at a 130 knot cruise. The deflection of four points on the rear of the tail boom relative to the position of these points for the unloaded, undamaged condition of the tail boom was used as a measure of the loss of structural rigidity. The same procedure was then used with the material properties of the aluminum alloys replaced with the material properties of T300/5208 high strength graphite/epoxy fibrous composite material, (0, + or - 45, 90)s for the skin and (0, + or - 45)s for the longerons, stringers, and bulk heads.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 161-172
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  • 83
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    Ring element dynamic stresses (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The stresses in the CTRAPRG and CTRIARG ring elements are not calculated for any of the dynamic solutions in the current COSMIC version of NASTRAN. A DMAP alter sequence for Solution 8 and post-processing program, NASTPOST, are presented to calculate these stresses. Test cases are used which describe the method. The stiffness and the consistent versus concentrated mass problems ascribed to this element are reviewed. The DMAP alter sequence introduces Solution 8 displacements to a Solution 1 module to calculate real and imaginary stress components during the execution of Solution 8. The post-processor, NASTPOST, calculates the magnitude/phase stress results. The DMAP sequence was written specifically for level 52 MSC/NASTRAN, but can certainly be used for any COSMIC version with slight modification.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 63-78
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  • 84
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    Improvements in sparse matrix operations of NASTRAN (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A "nontransmit" packing routine was added to NASTRAN to allow matrix data to be refered to directly from the input/output buffer. Use of the packing routine permits various routines for matrix handling to perform a direct reference to the input/output buffer if data addresses have once been received. The packing routine offers a buffer by buffer backspace feature for efficient backspacing in sequential access. Unlike a conventional backspacing that needs twice back record for a single read of one record (one column), this feature omits overlapping of READ operation and back record. It eliminates the necessity of writing, in decomposition of a symmetric matrix, of a portion of the matrix to its upper triangular matrix from the last to the first columns of the symmetric matrix, thus saving time for generating the upper triangular matrix. Only a lower triangular matrix must be written onto the secondary storage device, bringing 10 to 30% reduction in use of the disk space of the storage device.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 14-48
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  • 85
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    Corotational velocity strain formulations for nonlinear analysis of beams and axisymmetric shells (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Finite element formulations for large strain, large displacement problems are formulated using a kinematic description based on the corotational components of the velocity strain. The corotational components are defined in terms of a system that rotates with each element and approximates the rotation of the material. To account for rotations of the material relative to this element system, extra terms are introduced in the velocity strain equations. Although this formulation is incremental, in explicitly integrated transient problems it compares very well with formulations that are not.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 263-276
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  • 86
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    Finite elements for contact problems in two-dimensional elastodynamics (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A finite element approach for contact problems in two dimensional elastodynamics was proposed. Sticking, sliding, and frictional contact were taken into account. The method consisted of a modification of the shape functions, in the contact region, in order to involve the nodes of the contacting body. The formulation was symmetric (both bodies were contactors and targets), in order to avoid interpenetration. Compatibility over the interfaces was satisfied. The method was applied to the impact of a block on a rigid target. It is shown that the formulation can be applied to fluid structure interaction, and to problems involving material nonlinearity.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 225-235
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    Post-buckling behavior of a beam-column on a nonlinear elastic foundation with a gap (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The structural behavior of an elastic beam-column placed with a gap between two nonlinearity elastic layers each resting on a rigid foundation was examined. The beam-column was laterally supported at both ends and subjected to a uniform transverse load and axial compression. Its slenderness was such that the axial compressive force exceeds the amount that would be necessary to buckle it as a simple supported column. The elastic layers were represented by an elastic foundation with a strongly nonlinear specific reaction taken as a rapidly increasing function of the layer compression. The analytical model developed simulated the entire pattern of the deflection and stress state including layer and end support reactions, under gradually increasing axial force.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 165-173
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    Straightening of a wavy strip: An elastic-plastic contact problem including snap-through (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The nonlinear behavior of a wave like deformed metal strip during the levelling process were calculated. Elastic-plastic material behavior as well as nonlinearities due to large deformations were considered. The considered problem lead to a combined stability and contact problem. It is shown that, despite the initially concentrated loading, neglecting the change of loading conditions due to altered contact domains may lead to a significant error in the evaluation of the nonlinear behavior and particularly to an underestimation of the stability limit load. The stability was examined by considering the load deflection path and the behavior of a load-dependent current stiffness parameter in combination with the determinant of the current stiffness matrix.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 175-185
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    Computational strategy for the solution of large strain nonlinear problems using the Wilkins explicit finite-difference approach (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The STEALTH code system, which solves large strain, nonlinear continuum mechanics problems, was rigorously structured in both overall design and programming standards. The design is based on the theoretical elements of analysis while the programming standards attempt to establish a parallelism between physical theory, programming structure, and documentation. These features have made it easy to maintain, modify, and transport the codes. It has also guaranteed users a high level of quality control and quality assurance.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 97-114
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    Newton's method: A link between continuous and discrete solutions of nonlinear problems (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Newton's method for nonlinear mechanics problems replaces the governing nonlinear equations by an iterative sequence of linear equations. When the linear equations are linear differential equations, the equations are usually solved by numerical methods. The iterative sequence in Newton's method can exhibit poor convergence properties when the nonlinear problem has multiple solutions for a fixed set of parameters, unless the iterative sequences are aimed at solving for each solution separately. The theory of the linear differential operators is often a better guide for solution strategies in applying Newton's method than the theory of linear algebra associated with the numerical analogs of the differential operators. In fact, the theory for the differential operators can suggest the choice of numerical linear operators. In this paper the method of variation of parameters from the theory of linear ordinary differential equations is examined in detail in the context of Newton's method to demonstrate how it might be used as a guide for numerical solutions.
    Keywords: STRUCTURAL MECHANICS
    Type: Res. in Nonlinear Struct. and Solid Mech.; p 27-46
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    Analysis of reinforced concrete structures with occurrence of discrete cracks at arbitrary positions (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A nonlinear analysis of in-plane loaded plates is presented, which eliminates the disadvantages of the smeared crack approach. The elements used and the computational method are discussed. An example is shown in which one or more discrete cracks are dominant.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 1-12
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    Computational models for the nonlinear analysis of reinforced concrete plates (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A finite element computational model for the nonlinear analysis of reinforced concrete solid, stiffened and cellular plates is briefly outlined. Typically, Mindlin elements are used to model the plates whereas eccentric Timoshenko elements are adopted to represent the beams. The layering technique, common in the analysis of reinforced concrete flexural systems, is incorporated in the model. The proposed model provides an inexpensive and reasonably accurate approach which can be extended for use with voided plates.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 13-26
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    Elastic-plastic analysis using a triangular ring element in NASTRAN (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An elastic plastic triangular ring element is implemented in NASTRAN computer program. The plane strain problem of partially plastic thick walled cylinder under internal pressure is solved and compared with the earlier finite difference solution. A very good agreement has been reached. In order to demonstrate its application to more general problems, an overloaded thread problem for the British Standard Buttress is examined. The maximum axial and principal stresses are located and their values are determined as functions of loadings.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 190-200
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    An enhancement of NASTRAN for the seismic analysis of structures (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: New modules, bulk data cards and DMAP sequence were added to NASTRAN to aid in the seismic analysis of nuclear power plant structures. These allow input consisting of acceleration time histories and result in the generation of acceleration floor response spectra. The resulting system contains numerous user convenience features, as well as being reasonably efficient.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Kennedy Space Center 9th NASTRAN (R) Users' Colloq.; p 79-95
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  • 95
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    Microcomputer system for medium-sized and experimental finite element analysis (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The development of a microcomputer system is described. A series of finite element analysis programs are evaluated in terms of their cost effective application within the microcomputer system. It is shown that the system is practically maintenance free and can be sustained by individual laboratories of standard scale in the educational or academic environment.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 277-289
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    Nonlinear soil-structure interaction calculations simulating the SIMQUAKE experiment using STEALTH 2D (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Transient, nonlinear soil-structure interaction simulations of an Electric Power Research Institute, SIMQUAKE experiment were performed using the large strain, time domain STEALTH 2D code and a cyclic, kinematically hardening cap soil model. Results from the STEALTH simulations were compared to identical simulations performed with the TRANAL code and indicate relatively good agreement between all the STEALTH and TRANAL calculations. The differences that are seen can probably be attributed to: (1) large (STEALTH) vs. small (TRANAL) strain formulation and/or (2) grid discretization differences.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Research Center Res. in Nonlinear Struct. and Solid Mech.; p 47-66
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    Application of a data base management system to a finite element model (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In today's software market, much effort is being expended on the development of data base management systems (DBMS). Most commercially available DBMS were designed for business use. However, the need for such systems within the engineering and scientific communities is becoming apparent. A potential DBMS application that appears attractive is the handling of data for finite element engineering models. The applications of a commercially available, business-oriented DBMS to a structural engineering, finite element model is explored. The model, DBMS, an approach to using the DBMS, advantages and disadvantages are described. Plans for research on a scientific and engineering DBMS are discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Goddard Space Flight Center Eighth NASTRAN User's Colloq.; p 223-234
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    Applications of NASTRAN in Gust Response Analysis at Northrop (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A comprehensive gust response analysis was performed on a complete model of an airplane using the NASTRAN aeroelastic package. The analysis investigated random response to atmospheric turbulence and transient response to a discrete gust, including control system dynamics in both cases. It is shown that NASTRAN is an effective tool for aeroelastic analysis and active control system design.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Goddard Space Flight Center Eighth NASTRAN User's Colloq.; p 165-188
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    Condensing loaded points for transients by substructuring (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A technique for condensing dynamic loading points is described. The method was applied to substructure transient solutions and was found to be very effective.
    Keywords: STRUCTURAL MECHANICS
    Type: Eighth NASTRAN User's Colloq.; p 79-100
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    Stress concentrations in screw threads (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The concept of stress concentration in screw threads was defined using the sheer transfer rate as the fundamental quantity. The stress concentration is plotted for a fixed geometry. The Heywood equation was used to generate the basic plots and NASTRAN was used to extend the analysis to the case both where flanks of an individual thread tooth are in contact. The case where a finite axial stress is superimposed is discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Goddard Space Flight Center Eighth NASTRAN User's Colloq.; p 65-77
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