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  • STRUCTURAL MECHANICS  (600)
  • 2025-2025
  • 1980-1984  (277)
  • 1975-1979
  • 1970-1974  (323)
  • 1925-1929
  • 1983  (277)
  • 1971  (323)
Collection
Years
  • 2025-2025
  • 1980-1984  (277)
  • 1975-1979
  • 1970-1974  (323)
  • 1925-1929
Year
  • 1
    Publication Date: 2005-11-27
    Description: Fatigue crack length relationship with aircraft inspection intervals and structural reinforcement, high strength materials, and aircraft usage effects
    Keywords: STRUCTURAL MECHANICS
    Type: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 391-401
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  • 2
    Publication Date: 2005-11-27
    Description: Vibration design and test criteria considerations for space shuttle
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 423-450
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  • 3
    Publication Date: 2005-11-27
    Description: Optimization of payload for space shuttle by reducing structural loading and weight
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 315-332
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  • 4
    Publication Date: 2005-11-27
    Description: Buffet response of straight wing and delta wing model of space shuttle launch configuration
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 265-291
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  • 5
    Publication Date: 2005-11-27
    Description: Transonic wind tunnel investigation of flow characteristics and pressure fluctuation of space shuttle launch and reentry configurations
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 293-314
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  • 6
    Publication Date: 2005-11-27
    Description: Parameters contributing to aeroelastic problems in thermal protection of space shuttle
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 247-264
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  • 7
    Publication Date: 2005-11-27
    Description: Application of research in panel flutter and boundary layer thickness to space shuttle
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 231-245
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  • 8
    Publication Date: 2005-11-27
    Description: Transonic flutter and buffeting for elastic wind tunnel models of straight wing proposed for space shuttles
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 201-229
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  • 9
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    Publication Date: 2005-11-27
    Description: Problems in propellant dynamics including pipeline dynamics, effect of bubble location, turbulent flow, and effect of tilting tank on liquid oscillation frequency
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 95-120
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  • 10
    Publication Date: 2005-11-27
    Description: Dynamic response of thermal protection system panel for space shuttle
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. LANGLEY RES. CENTER NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 49-93
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  • 11
    Publication Date: 2005-11-27
    Description: Vibration tests of space shuttle panels at room temperature
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 27-48
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  • 12
    Publication Date: 2005-11-27
    Description: Vibration studies of dynamic scale model of space shuttle
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 1-25
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  • 13
    Publication Date: 2011-08-16
    Description: Elastic harmonic waves propagation in composite circular elastic cylinder
    Keywords: STRUCTURAL MECHANICS
    Type: ; VUE SCIENTIFIQUE ET
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  • 14
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    Publication Date: 2011-08-16
    Description: The nature of aerospace noise-induced vibration problems is summarized, with emphasis placed on reviewing and categorizing types and sources of noise which are significant in such problems. Physical characteristics of representative noise loads associated with propellers, turbojet engine exhausts, and sonic boom waves are presented. Examples of noise-induced structural vibrations are discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: Sound and Vibration; 5; Dec. 197
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  • 15
    Publication Date: 2011-08-16
    Description: Collection of theoretical and experimental studies covering basic mechanisms of fatigue in the subcreep and creep ranges, fatigue damage detection, field practices for fatigue damage repair in jet engine components, and fatigue damage avoidance and control. Individual items are abstracted in this issue.
    Keywords: STRUCTURAL MECHANICS
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  • 16
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    Publication Date: 2011-08-16
    Description: A summary is presented of various methods available to the engineer for dealing with fatigue problems. Design, metallurgical, and service factors are considered. An attempt is made to provide a rational basis for each approach, resorting in each case to an understanding of the fundamental mechanism of the fatigue process.
    Keywords: STRUCTURAL MECHANICS
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  • 17
    Publication Date: 2011-08-16
    Description: The magnitude of the previously observed effect associated with laminated composites - i.e., that a coupling exists between extension and bending if the plies are not balanced in number and fiber orientation - is investigated for buckling and vibration of doubly curved monocoque plates and shells of positive and negative Gaussian curvature. In addition, the effect of stacking sequence is examined. Solutions are presented which provide a means of simply and economically assessing the magnitude of the coupling and stacking effects for various composite materials and geometric configurations.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Composite Materials; 5; Oct. 197
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  • 18
    Publication Date: 2011-08-16
    Description: Structural panel under acoustic loading by supersonic convected turbulence, deriving responses with finite Fourier transforms
    Keywords: STRUCTURAL MECHANICS
    Type: ; - DISCRETE CONTROL S
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  • 19
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    Publication Date: 2011-08-16
    Description: Reliability prediction of narrow band structures under random excitations, considering catastrophic and fatigue failure modes
    Keywords: STRUCTURAL MECHANICS
    Type: ; - DISCRETE CONTROL S
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  • 20
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    Publication Date: 2011-08-16
    Description: Convergent finite element equations for dynamic stability of plates dependent on vibration and buckling modes
    Keywords: STRUCTURAL MECHANICS
    Type: ; ADEMIE DES SCIENCES
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  • 21
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    Publication Date: 2011-08-16
    Description: Symmetric and asymmetric dynamic buckling of shallow elastic arches under uniform loads, using nonlinear finite difference method
    Keywords: STRUCTURAL MECHANICS
    Type: ; ADEMIE DES SCIENCES
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  • 22
    Publication Date: 2011-08-16
    Description: Variational principles for initial boundary value problem of fully coupled linear thermoelasticity for inhomogeneous anisotropic materials with microstructure
    Keywords: STRUCTURAL MECHANICS
    Type: ; ADEMIE DES SCIENCES
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  • 23
    Publication Date: 2011-08-16
    Description: Vibration response NDT for fatigue crack damage in laminated filament-reinforced epoxy composites
    Keywords: STRUCTURAL MECHANICS
    Type: ; YAL SOCIETY (
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  • 24
    Publication Date: 2011-08-16
    Description: Thin shell isotropic clamped free elliptical cylindrical shells with various cross sectional eccentricities, measuring frequencies and mode shapes by vibration analysis
    Keywords: STRUCTURAL MECHANICS
    Type: ; YAL SOCIETY (
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  • 25
    Publication Date: 2011-08-16
    Description: Space shuttle structures and materials, considering booster arrangements thermal protection, high temperature metals and composite materials
    Keywords: STRUCTURAL MECHANICS
    Type: ; VUE SCIENTIFIQUE ET
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  • 26
    Publication Date: 2011-08-16
    Description: Structural dynamic responses as nonstationary narrow band random process, establishing peak values distribution functions with frequency interpretation
    Keywords: STRUCTURAL MECHANICS
    Type: ; 715-727. (
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  • 27
    Publication Date: 2011-08-16
    Description: Plate excitation by supersonic turbulent and shock boundary layers, measuring wall pressure fluctuation and panel displacement
    Keywords: STRUCTURAL MECHANICS
    Type: ; - DISCRETE CONTROL S
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  • 28
    Publication Date: 2011-08-16
    Description: Spacecraft structures weight optimization based on fracture mechanics and reliability cost constraints applied to pressure vessel design
    Keywords: STRUCTURAL MECHANICS
    Type: ; IENCES (
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  • 29
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    Publication Date: 2011-08-16
    Description: Defense of damping theory applications in flutter analysis, discussing energy dissipation
    Keywords: STRUCTURAL MECHANICS
    Type: ; SEARCH(
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  • 30
    Publication Date: 2011-08-16
    Description: Discussion of a large NASA-sponsored digital computer program for static and dynamic analysis of structures with linear or nonlinear material properties. The program fits to perform buckling analysis, vibration mode analysis of conservative or damped systems, frequency response analysis, and transient response analysis on the IBM 360, UNIVAC 1108, and CDC 6600 computers. It also provides automatic generation of several types of loads such as gravity loads and thermal strain loads, plots of deformed and nondeformed structures, and the choice of alternate analysis methods such as direct or modal formulations of dynamic problems. The program is intended primarily for large problems involving hundreds of thousands of degrees of freedom. A flexible Executive System is provided to facilitate the addition of new functional capabilities to the program.
    Keywords: STRUCTURAL MECHANICS
    Type: Computers and Structures; 1; Oct. 197
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  • 31
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    Publication Date: 2011-08-16
    Description: Prediction of the shear flow around bodies impulsively set into motion at a uniform velocity. Information is presented on the local wall shear stress, velocity distribution, steady flow times, and thermal response for wedge flows where local flow acceleration occurs. The essential features of the flow field are found to be describable by the approximate series expansion method of Goldstein and Rosenhead (1936). This method would appear to be useful in rapidly calculating the viscous drag on the forward face of various shaped bodies where local flow acceleration occurs.
    Keywords: STRUCTURAL MECHANICS
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  • 32
    Publication Date: 2011-08-16
    Description: The framework of a new method is outlined for treating creep-fatigue behavior of metals. Inelastic strain-ranges are partitioned into the components of (1) completely reversed plasticity, (2) tensile plasticity reversed by compressive creep, or tensile creep reversed by compressive plasticity, and (3) completely reversed creep. Each of these components is shown to be related to cyclic life by a Manson-Coffin type power-law equation. A linear life fraction rule is used to combine the damaging effects of the individual components enabling the prediction of life. Test results are presented for a 2.25 Cr-1 Mo steel as well as limited information for a Type 316 stainless steel.
    Keywords: STRUCTURAL MECHANICS
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  • 33
    Publication Date: 2011-08-19
    Description: A constitutive theory is presented for representing the anisotropic viscoplastic behavior of high-temperature alloys that possess directional properties resulting from controlled grain growth or solidification. The theory is an extension of a viscoplastic model that has been applied in structural analyses involving isotropic metals. Anisotropy is introduced through the definition of a vector field that identifies a preferential (solidification) direction at each material point. Following the development of a full multiaxial theory, application is made to homogeneously stressed elements in pure shear and to a uniaxially stressed rectangular block in plane stress with the stress direction oriented at an arbitrary angle with the material direction. It is shown that an additional material parameter introduced to characterize the degree of anisotropy can be determined on the basis of simple creep tests.
    Keywords: STRUCTURAL MECHANICS
    Type: Nuclear Engineering and Design (ISSN 0029-5493); 83; 389-396
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  • 34
    Publication Date: 2011-08-18
    Description: The force input mobility of an infinite elastic circular cylindrical shell filled with fluid is derived by using the spectral equations of motion. Mobilities are evaluated and their physical interpretations are discussed for a steel shell of thickness h/a = 0.05 filled with water and vibrating in the n = 0, 1 and 2 circumferential modes. The results are subsequently used to analyze the related situations of wave transmission through a radial ring constraint and the far field vibrational energy distributions between the contained fluid and the shell wall for line and point driving forces.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Sound and Vibration (ISSN 0022-460X); 87; 409-427
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  • 35
    Publication Date: 2011-08-18
    Description: The boundary collocation method was used to generate Mode 1 stress intensity and crack mouth opening displacement coefficients for externally radially cracked ring segments subjected to three point radial loading. Numerical results were obtained for ring segment outer-to-inner radius ratios (R sub o/R sub i) ranging from 1.10 to 2.50 and crack length to segment width ratios (a/W) ranging from 0.1 to 0.8. Stress intensity and crack mouth displacement coefficients were found to depend on the ratios R sub o/R sub i and a/W as well as the included angle between the directions of the reaction forces. Previously announced in STAR as N83-35413
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Testing and Evaluation (ISSN 0090-3973); 11; 357-359
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  • 36
    Publication Date: 2011-08-18
    Description: Two methods for identifying the mass, damping and stiffness matrices of a linear vibrating system are presented. Both methods require the measurement of acceleration, velocity and displacement at various locations of the system. In the first method, the response of the system subjected to known forces is used while the second method employs the free vibration data. The unknown parameters are recovered through the standard least squares procedure. Numerical results are presented for several examples.
    Keywords: STRUCTURAL MECHANICS
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 511-520
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  • 37
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    Publication Date: 2011-08-18
    Description: The problem of potential instability caused by actuator dynamics is examined. Two ways of overcoming it are discussed: rate feedback with compensation and position feedback with tuning filters.
    Keywords: STRUCTURAL MECHANICS
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 119-142
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  • 38
    Publication Date: 2011-08-18
    Description: (Previously announced in STAR as N82-24501)
    Keywords: STRUCTURAL MECHANICS
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  • 39
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    Publication Date: 2011-08-18
    Description: Problems encountered by aerospace designers in attempting to optimize whole aircraft are discussed, along with possible solutions. Large scale optimization, as opposed to component-by-component optimization, is hindered by computational costs, software inflexibility, concentration on a single, rather than trade-off, design methodology and the incompatibility of large-scale optimization with single program, single computer methods. The software problem can be approached by placing the full analysis outside of the optimization loop. Full analysis is then performed only periodically. Problem-dependent software can be removed from the generic code using a systems programming technique, and then embody the definitions of design variables, objective function and design constraints. Trade-off algorithms can be used at the design points to obtain quantitative answers. Finally, decomposing the large-scale problem into independent subproblems allows systematic optimization of the problems by an organization of people and machines.
    Keywords: STRUCTURAL MECHANICS
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  • 40
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    Publication Date: 2011-08-18
    Description: A simplified buckling analysis is presented for a family of periodic lattice structures such as those proposed for large space structures. A transcendental 6 x 6 matrix of eigenvalues is shown to be sufficient for modeling buckling behavior because member stiffnesses are based on an exact solution of the beam-column equation. Exact stiffnesses are derived for a curved member, thus allowing modeling of imperfect lattice structures. Comparisons of predictions of the lattice model with those available from shell and beam theory underscore the inaccuracies introduced by treating the lattice structure as a continuum. Sample calculations are provided for an isogrid cylinder and a three element double-laced truss.
    Keywords: STRUCTURAL MECHANICS
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  • 41
    Publication Date: 2011-08-18
    Description: Truss beams with members having viscous damping are modeled with a Timoshenko beam. Procedures for deriving the equivalent bending rigidity, transverse shear rigidity, and damping are presented. Explicit expressions for these equivalent beam properties are obtained for a specific truss beam. The beam model thus established is then used to investigate the effect of damping in free vibration. Finally, the beam is employed in the estimation of structural parameters in a simply-supported truss beam using a random search algorithm.
    Keywords: STRUCTURAL MECHANICS
    Type: JPL Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 531-545
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  • 42
    Publication Date: 2011-08-18
    Description: A general approach for distributed parameter modeling of complex dynamical systems is described. The method consists of dividing the system in parts which can be modeled by simple partial differential equations and coupling the equations thus obtained by applying Hamilton's variational formalism to the entire system. The modeling of a large, offset-fed, wrap-rib antenna is presented to illustrate the approach. Although such models are perhaps not as precise as finite element models, they can be useful for initial physical insight and parametric design.
    Keywords: STRUCTURAL MECHANICS
    Type: Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 89-102
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  • 43
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    Publication Date: 2011-08-18
    Description: The hybrid experimental-numerical stress-analysis technique, which saw limited applications during the 1950's, has been resurrected with the vastly improved numerical techniques of the 1970's. By inputing the experimental results as initial and boundary conditions, modern computer codes are executed in its generation and application modes to yield results which are unobtainable when only one of the two techniques is used. The hybrid technique thus exemplifies the complementary role of the experimental and numerical techniques.
    Keywords: STRUCTURAL MECHANICS
    Type: (ISSN 0014-4851)
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  • 44
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    Publication Date: 2011-08-18
    Description: Fourier transforms and the Wiener-Hopf technique are used in conjunction with plane elastostatics to examine the singular crack tip stress field in the double cantilever beam (DCB) specimen. In place of the Dirac delta function, a family of functions which duplicates the important features of the concentrated forces without introducing unmanageable mathematical complexities is used as a loading function. With terms of order h-squared/a-squared retained in the series expansion, the dimensionless stress intensity factor is found to be K (h to the 1/2)/P = 12 to the 1/2 (a/h + 0.6728 + 0.0377 h-squared/a-squared), in which P is the magnitude of the concentrated forces per unit thickness, a is the distance from the crack tip to the points of load application, and h is the height of each cantilever beam. The result is similar to that obtained by Gross and Srawley by fitting a line to discrete results from their boundary collocation analysis.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal of Fracture (ISSN 0376-9429); 22; June 198
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  • 45
    Publication Date: 2011-08-18
    Description: A fracture mechanics approach to the well-known delamination problem in composite materials is presented. Based on the theory of anisotropic laminate elasticity and interlaminar fracture mechanics concepts, the composite delamination problem is formulated and solved. The exact order of the delamination crack-tip stress singularity is determined. Asymptotic stress and displacement fields for an interlaminar crack are obtained. Fracture mechanics parameters such as mixed-mode stress intensity factors, KI, KII, KIII, and the energy release rate, G, for composite delamination problems are defined. To illustrate the fundamental nature of the delamination crack behavior, solutions for edge-delaminated graphite-epoxy composites under uniform axial extension are presented. Effects of fiber orientation, ply thickness, and delamination length on the interlaminar fracture are examined.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Composite Materials (ISSN 0021-9983); 17; May 1983
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  • 46
    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2112, Accession no. A82-30182
    Keywords: STRUCTURAL MECHANICS
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  • 47
    Publication Date: 2011-08-18
    Description: Stress-intensity factors are obtained for point loaded equal length cracks 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 stress-intensity factors in the case of (1) biaxial tension and pure shear of an infinite plate and (2) tension and pin loading of a plate with cracks emanating from one hole in a row of holes.
    Keywords: STRUCTURAL MECHANICS
    Type: Res Mechanica (ISSN 0143-0084); 9; 2, 19; 1983
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  • 48
    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2111, Accession no. A82-30171
    Keywords: STRUCTURAL MECHANICS
    Type: (ISSN 0021-8669)
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  • 49
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2110, Accession no. A82-30166
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  • 50
    Publication Date: 2014-12-18
    Description: Module design modification requirements for incorporating aeroelastic capabilities into NASTRAN structural analysis program
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 779-795
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  • 51
    Publication Date: 2016-06-07
    Description: The objectives of the hot section technology (HOST) burner liner cyclic rig test program are basically threefold: (1) to assist in developing predictive tools needed to improve design analyses and procedures for the efficient and accurate prediction of burner liner structural response; (2) to calibrate, evaluate and validate these predictive tools by comparing the predicted results with the experimental data generated in the tests; and (3) to evaluate existing as well as advanced temperature and strain measurement instrumentation, both contact and noncontact, in a simulated engine cycle environment. The data generated will include measurements of the thermal environment (metal surface temperatures) as well as structural (strain) and life (fatigue) responses of simulated burner liners and specimens under controlled boundary and operating conditions. These data will be used to calibrate, compare and validate analytical theories, methodologies and design procedures, as well as improvements in them, for predicting liner temperatures, stress-strain responses and cycles to failure. Comparison of predicted results with experimental data will be used to show where the predictive theories, etc. need improvements. In addition, as the predictive tools, as well as the tests, test methods, and data acquisition and reduction techniques, are developed and validated, a proven, integrated analysis/experiment method will be developed to determine the cyclic life of a simulated burner liner.
    Keywords: STRUCTURAL MECHANICS
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 181-193
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  • 52
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    Publication Date: 2016-06-07
    Description: The HOST Liner Cyclic Program is utilizing two types of test apparatus, rectangular box rigs and a full annular rig. To date two quartz lamp cyclic box rigs have been tested and a third is to begin testing in late October 1983. The box rigs are used to evaluate 5x8 inch rectangular linear samples. A 21 inch diameter outer liner simulator is also being built up for testing beginning in April 1984. All rigs are atmospheric rigs. The first box rig, a three 6-kVA lamp installation, was operated under adverse conditions to determine feasibility of using quartz lamps for cyclic testing. This work was done in December 1981 and looked promising. The second box rig, again using three 6-kVA lamps, was operated to obtain instrumentation durability information and initial data input to a Finite Element Model. This limited test program was conducted in August 1983. Five test plates were run. Instrumentation consisted of strain gages, thermocouples and thermal paint. The strain gages were found to fail at 1200 F as expected though plates were heated to 1700 F. The third box rig, containing four 6-kVA lamps, is in build up for testing to begin in late October 1983. In addition to 33 percent greater power input, this rig has provision for 400 F backside line cooling air and a viewing port suitable for IR camera viewing. The casing is also water cooled for extended durability.
    Keywords: STRUCTURAL MECHANICS
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 195-204
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  • 53
    Publication Date: 2016-06-07
    Description: The objective of this program is to produce a series of new computer codes that permit more accurate and efficient three dimensional inelastic analysis of selected hot section components - combustor liners, turbine blades and turbine vanes. The computer codes embody a progression of mathematical models and are streamlined to take advantage of geometrical features, loading conditions, and forms of material response that distinguish each group of selected components.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 179-180
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  • 54
    Publication Date: 2016-06-07
    Description: The objective of this research is to develop an analytical tool capable of economically evaluating the cyclic time dependent plasticity which occurs in hot section engine components in areas of strain concentration resulting from the combination of both mechanical and thermal stresses. The techniques developed must be capable of accommodating large excursions in temperatures with the associated variations in material properties including plasticity and creep. The overall objective of this proposed program is to develop advanced 3-D inelastic structural/stress analysis methods and solution strategies for more accurate and yet more cost effective analysis of combustors, turbine blades, and vanes. The approach will be to develop four different theories, one linear and three higher order with increasing complexities including embedded singularities.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Lewis Research Center Turbine Eng. Hot Sect. Technol. (HOST); p 175-177
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  • 55
    Publication Date: 2014-09-11
    Description: The dynamic characteristics of the Solar Array Flight Experiment (SAFE) structure during deployment and retraction are investigated. The SAFE structure consists of a deployable mast with an attached solar blanket designed with accordion type folds to permit packaging in a small volume. The planar form of the blanket geometry during deployment is maintained by a blanket tension/guidewire system. Structurally, the mast is modeled as an Euler beam column with inplane and out of plane bending and finite torsional stiffness. For out of plane motion, the blanket is modeled as a distributed mass uniformly supported by the three guidewires. For inplane motion the blanket displacements are assumed to vary linearly from the mast base to the mast tip. The mathematical model uses a virtual work formulation, required because the axial loading on the mast is nonconservative, combined with assumed beam modes to derive the differential equations of motion. Consideration of the time dependent boundary conditions results in an infinite set of ODE with time dependent coefficients. Finally, correlation of mast tip accelerations to mast base bending moments for specified modal motions are indicated.
    Keywords: STRUCTURAL MECHANICS
    Type: Res. Rept.: 1983 NASA(ASEE Summer Faculty Fellowship Program; 24 p
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  • 56
    Publication Date: 2014-09-11
    Description: Traditional composite lamination theory was used to predict composite graphite-epoxy laminate stiffnesses for comparison to quasi-experimental stiffnesses developed from cylindrical bottle pressure testing. Stiffness sensitivities were examined for variations in constituent materials and geometric properties. The material component interactions examined were the fiber longitudinal and transverse Young's modulus, the fiber shear modulus and primary Poisson's ratio, the resin Young's modulus, shear modulus, and Poisson's ratio. The geometric variation of the helical winding angle was also examined. Two computer programs were written to generate the data used to demonstrate the stiffness variations.
    Keywords: STRUCTURAL MECHANICS
    Type: Alabama Univ. Res. Rept.: 1983 NASA(ASEE Summer Faculty Fellowship Program; 34 p
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  • 57
    Publication Date: 2014-09-04
    Description: Reduction of proliferation and maintainability of finite element method computer programs
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 813-825
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  • 58
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    Publication Date: 2014-09-04
    Description: Coding considerations for implementation of general isoparametric solid elements into NASTRAN displacement method program for stress analysis
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 797-811
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  • 59
    Publication Date: 2014-09-04
    Description: NASTRAN and substructuring techniques for structural analysis of complex space shuttle structures
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 769-778
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  • 60
    Publication Date: 2014-09-04
    Description: NASTRAN flat plate finite element convergence properties for stress analysis of cylindrical and conical shells
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 749-767
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  • 61
    Publication Date: 2014-09-03
    Description: Normal mode determination of RAE antennas and spacecraft for in-flight configuration using computer simulation
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 237-249
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  • 62
    Publication Date: 2014-09-10
    Description: An experiment to measure the elastic deflection of the DSS 14 concrete pedestal under the weight of the antenna was conducted in February 1983 and is compared to a similiar experiment made in 1968. Comparison of the results confirms the decrease in elastic modulus measured on core samples recently taken from the pedestal.
    Keywords: STRUCTURAL MECHANICS
    Type: The Telecommun. and Data Acquisition Rept.; p 89-91
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  • 63
    Publication Date: 2014-09-03
    Description: Comparison of finite element computer programs for analysis of clamped flat plate and built-up wing vibration frequencies
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 637-646
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  • 64
    Publication Date: 2014-09-03
    Description: Dynamic characteristics of space shuttle determined by NASTRAN
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 421-437
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  • 65
    Publication Date: 2014-09-03
    Description: Structural dynamic analysis of electronic assemblies subjected to random vibration loads
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 363-391
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  • 66
    Publication Date: 2014-09-03
    Description: Modal analysis of response and fatigue of aluninum aircraft panels modal response
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 343-361
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  • 67
    Publication Date: 2014-09-03
    Description: NASTRAN application to static stress and dynamic modal problems of horizontal stabilizer of F-14A aircraft
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 251-264
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  • 68
    Publication Date: 2014-09-03
    Description: Application of NASTRAN to structural analysis of space shuttle orbiter finite element model with over 3000 joint degrees of freedom
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 451-464
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  • 69
    Publication Date: 2014-09-03
    Description: Analytical procedures for predicting coupled fluid structural responses of aircraft hydraulic systems
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 407-419
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  • 70
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    Publication Date: 2014-09-03
    Description: NASTRAN program for calculating structural vibration characteristics of plate configurations
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 325-341
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  • 71
    Publication Date: 2011-08-18
    Description: An unconditionally stable implicit-explicit method is proposed for the analysis of transient coupled thermal stress waves, and the computer-implementation aspects of the method are discussed. In the method proposed here, the mechanical displacement and temperature are used as independent variables. The resulting coupled finite element matrix equations are symmetric.
    Keywords: STRUCTURAL MECHANICS
    Type: Computers and Structures (ISSN 0045-7949); 17; 3, 19; 1983
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  • 72
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2112, Accession no. A82-30186
    Keywords: STRUCTURAL MECHANICS
    Type: (ISSN 0001-1452)
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  • 73
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2108, Accession no. A82-30124
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal (ISSN 0001-1452); 21; 1729-173
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  • 74
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 01, p. 60, Accession no. A83-10900
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft (ISSN 0021-8669); 20; 907-912
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  • 75
    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2109, Accession no. A82-30152
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft (ISSN 0021-8669); 20; 899-906
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  • 76
    Publication Date: 2011-08-18
    Description: A fracture mechanics analysis has been developed that describes the progress of delamination damage in composite plates struck by a hard spherical object. The analysis is based on large deflection plate mechanics for circular isotropic plates wherein multiple axisymmetric delaminations grow. Test data show that the analysis predicts the influence of plate thickness, support conditions, and matrix toughness on the onset and propagation of delamination.
    Keywords: STRUCTURAL MECHANICS
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  • 77
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    Publication Date: 2011-08-18
    Description: A three-dimensional element based on the total Lagrangian description of large deformations of a layered anisotropic composite medium is developed, validated, and used to analyze layered composite shells. The element contains the following features: geometric nonlinearity, dynamic (transient) behavior, and arbitrary lamination scheme and lamina properties. Numerical results of nonlinear bending, natural vibration, and transient response are presented to illustrate the capabilities of the element.
    Keywords: STRUCTURAL MECHANICS
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  • 78
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    Publication Date: 2016-06-07
    Description: One of the primary drivers that prompted the initiation of the hot section technology (HOST) program was the recognized need for improved cyclic durability of costly hot section components. All too frequently, fatigue in one form or another was directly responsible for the less than desired durability, and prospects for the future weren't going to improve unless a significant effort was mounted to increase our knowledge and understanding of the elements governing cyclic crack initiation and propagation lifetime. Certainly one of the important factors is the ability to perform accurate structural stress-strain analyses on a routine basis to determine the magnitudes of the localized stresses and strains since it is these localized conditions that govern the initiation and crack growth processes. Developing the ability to more accurately predict crack initiation lifetimes and cyclic crack growth rates for the complex loading conditions found in turbine engine hot sections is of course the ultimate goal of the life prediction research efforts. It has been found convenient to divide the research efforts into those dealing with nominally isotropic and anisotropic alloys; the latter for application to directionally solidified and single crystal turbine blades.
    Keywords: STRUCTURAL MECHANICS
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 205-207
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  • 79
    Publication Date: 2016-06-07
    Description: The Hot Section Technology (HOST) Project is a NASA-sponsored endeavor to improve the durability of advanced gas turbine engines for commercial and military aircraft. Through improvements in the analytical models and life prediction systems, designs for future hot section components , the combustor and turbine, will be more accurately analyzed and will incorporate features required for longer life in the more hostile operating environment of high performance engines.
    Keywords: STRUCTURAL MECHANICS
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 1-6
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  • 80
    Publication Date: 2018-12-01
    Description: A review of developments in structural optimization techniques and their interface with growing computer capabilities is presented. Structural design steps comprise functional definition of an object, an evaluation phase wherein external influences are quantified, selection of the design concept, material, object geometry, and the internal layout, and quantification of the physical characteristics. Optimization of a fully stressed design is facilitated by use of nonlinear mathematical programming which permits automated definition of the physics of a problem. Design iterations terminate when convergence is acquired between mathematical and physical criteria. A constrained minimum algorithm has been formulated using an Augmented Lagrangian approach and a generalized reduced gradient to obtain fast convergence. Various approximation techniques are mentioned. The synergistic application of all the methods surveyed requires multidisciplinary teamwork during a design effort.
    Keywords: STRUCTURAL MECHANICS
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  • 81
    Publication Date: 2016-03-09
    Description: The mechanics of materials and material characterization are considered, taking into account micromechanics, the behavior of steel structures at elevated temperatures, and an anisotropic plasticity model for inelastic multiaxial cyclic deformation. Other topics explored are related to advances and trends in finite element technology, classical analytical techniques and their computer implementation, interactive computing and computational strategies for nonlinear problems, advances and trends in numerical analysis, database management systems and CAD/CAM, space structures and vehicle crashworthiness, beams, plates and fibrous composite structures, design-oriented analysis, artificial intelligence and optimization, contact problems, random waves, and lifetime prediction. Earthquake-resistant structures and other advanced structural applications are also discussed, giving attention to cumulative damage in steel structures subjected to earthquake ground motions, and a mixed domain analysis of nuclear containment structures using impulse functions.
    Keywords: STRUCTURAL MECHANICS
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  • 82
    Publication Date: 2014-09-03
    Description: Pre-processor, post-processor, and multiple level substructuring routines for data management in support of NASTRAN finite element structural analysis of spacecraft
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 697-707
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  • 83
    Publication Date: 2014-09-03
    Description: Evaluation of NASTRAN system based on large complex airframe analysis
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 493-515
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  • 84
    Publication Date: 2014-09-03
    Description: Structural analysis and design optimization of spacecraft using NASTRAN
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 479-491
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  • 85
    Publication Date: 2014-09-03
    Description: Use of NASTRAN as analysis tool in structural design optimization process applied to aircraft fuselage type structure
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 465-478
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  • 86
    Publication Date: 2014-09-03
    Description: NASTRAN adaptation to CDC 6600 computer system for analysis of Viking launch vehicle
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 265-284
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  • 87
    Publication Date: 2014-09-03
    Description: Comparison of ASKA and NASTRAN programs analyses of space shuttle hot elevon test article deformed under thermal and mechanical loads
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 163-180
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  • 88
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    Publication Date: 2014-09-03
    Description: NASTRAN computer program applications in stress analysis performed on Skylab hardware
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 27-46
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  • 89
    Publication Date: 2014-09-12
    Description: Static analysis and a computer structural model for the large 64-m antenna pedestal are developed using the MSC version of the NASTRAN program. This model was necessary to conduct a variety of hydrostatic bearing rehabilitation studies. The results obtained from the model show that the top surface deflections due to pad loads are in good agreement with the results previously obtained from a simplified "shortcut' analytical model, and also in agreement with field measurements. In addition, the displacement and force distributions as well as the state of stress and strain are obtained.
    Keywords: STRUCTURAL MECHANICS
    Type: The Telecommun. and Data Acquisition Rept.; p 86-96
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  • 90
    Publication Date: 2014-09-03
    Description: Dynamic response of cylindrical shell excited by simulated turbulent boundary layer pressure field determined by NASTRAN
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 393-405
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  • 91
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    In:  CASI
    Publication Date: 2014-09-03
    Description: Accuracy, adequacy, and limitations of NASTRAN computer program static load structural analysis solutions
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 47-63
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  • 92
    Publication Date: 2014-09-03
    Description: NASTRAN program used to calculate stress concentration caused by surface cavities in plates under biaxial loading
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 9-16
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  • 93
    Publication Date: 2014-09-03
    Description: Structural analysis of analytical dynamic space shuttle configuration models
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 221-236
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  • 94
    Publication Date: 2014-09-03
    Description: Structural analysis of uniform beam under various end conditions using finite element and analytic methods
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 181-199
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  • 95
    Publication Date: 2014-09-03
    Description: NASTRAN program differential stiffness method applied to structural analysis of Apollo Telescope Mount solar array wing and results compared with static load tests
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 107-121
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  • 96
    Publication Date: 2014-09-03
    Description: NASTRAN computer program differential stiffness and static load analysis methods compared for aircraft tandem side opening canopies
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 85-105
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  • 97
    Publication Date: 2014-09-03
    Description: NASTRAN computer program used to calculate lateral deflections of weak spacecraft antenna boom to determine stiffness at small strains
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences p17-26 (SEE 71-36253 22-32)
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  • 98
    Publication Date: 2014-09-03
    Description: Development, maintenenace, and future capabilities of NASTRAN - NASA Structural Analysis computer program
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users Experiences; p 1-7
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  • 99
    Publication Date: 2016-06-07
    Description: The empennage structure on the Learjet 55 aircraft was quite similar to the empennage structure on earlier Learjet models. However, due to an important structural change in the vertical fin along with the new loads environment on the 50 series aircraft, a structural test was required on the vertical fin, but the horizontal tail was substantiated by a comparative analysis with previous tests. NASTRAN analysis was used to investigate empennage deflections, stress levels, and control surface hinge forces. The hinge force calculations were made with the control surfaces in the deflected as well as undeflected configurations. A skin panel buckling analysis was also performed, and the non-linear effects of buckling were simulated in the NASTRAN model to more accurately define internal loads and stress levels. Comparisons were then made between the Model 55 and the Model 35/36 stresses and internal forces to determine which components were qualified by previous tests. Some of the methods and techniques used in this analysis are described.
    Keywords: STRUCTURAL MECHANICS
    Type: COSMIC 11th NASTRAN User's Colloq.; p 226-248
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  • 100
    Publication Date: 2016-06-07
    Description: The J-4 Rocket Test Cell and its Thrust Measuring System (TMS) at Arnold Engineering Development Center were modified to provide multicomponent force measurement of large solid rocket motors having nozzle gimbaling capability. To verify the structural integrity of a combined TMS and motor system, a large finite element model of the TMS and motor was developed using the NASTRAN computer program. Due to the importance of obtaining accurate estimates for the dynamic force levels, it was necessary to certify that the model adequately simulated the physical system. This was accomplished by performing a modal analysis test on the TMS and motor combination. The objectives were to discuss the physical characteristics of the TMS and motor that influence the NASTRAN model; to compare the frequency response characteristics computed using the NASTRAN model to those obtained from the modal analysis test; to discuss the experiences gained in modal analysis testing; and to demonstrate how state-of-the-art experimental and analytical methods are used in the design of ground test facilities.
    Keywords: STRUCTURAL MECHANICS
    Type: COSMIC 11th NASTRAN User's Colloq.; p 207-225
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