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  • MACHINE ELEMENTS AND PROCESSES  (51)
  • STRUCTURAL MECHANICS  (46)
  • ASTROPHYSICS
  • 1970-1974  (97)
  • 1973  (97)
  • 1963
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  • 1
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    BUCLAP2: A computer program for instability analysis of laminated long plates subjected to combined inplane loads. User's manual (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The usage of the computer program BUCLAP2 is described. The program is intended for linear instability analysis of long, rectangular flat and curved laminated plates with arbitrary orientation of orthotropic axes in each layer. The loadings considered are combinations of inplane normal and shear loads. Arbitray elastic boundary conditions are included for the sides of the plate Instructions for use of the program are included along with Input data requirements, output information, and sample problems. For program description, see .
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-132298 , D6-60187
    Format: application/pdf
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  • 2
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    BUCLAP2: A computer program for instability analysis of laminated long plates subjected to combined inplane loads (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This program description document describes the program structure and the design details of a CDC 6600 FORTRAN 4 digital computer program, BUCLAP2, which uses minimum energy principles to do an elastic stability analysis of curved and flat laminated rectangular long plates subjected to combined inplane normal and shear loads. Given the geometry, the material properties, and slected boundary conditions for the plate element, the program calculates the minimum buckling load for various wave lengths. The two parallel ends of the program calculates the minimum buckling load for various wave lengths. The two parallel ends of the long plate must be simply supported and arbitrary elastic boundary conditions may be imposed along either one or both external longitudinal sides. For guide to program use, see
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-132299
    Format: application/pdf
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  • 3
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    An economical method of analyzing transient motion of gas-lubricated rotor-bearing systems. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A method of economically evaluating the hydrodynamic forces generated in a gas-lubricated tilting-pad bearing is presented. The numerical method consists of solving the case of the infinite width bearing and then converting this solution to the case of the finite bearing by accounting for end leakage. The approximate method is compared to the finite-difference solution of Reynolds equation and yields acceptable accuracy while running about one-hundred times faster. A mathematical model of a gas-lubricated tilting-pad vertical rotor systems is developed. The model is capable of analyzing a two-bearing-rotor system in which the rotor center of mass is not at midspan by accounting for gyroscopic moments. The numerical results from the model are compared to actual test data as well as analytical results of other investigators.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: ASLE PREPRINT 73AM-2B-2 , Annual Meeting; Apr 30, 1973 - May 03, 1973; Chicago, IL
    Format: text
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  • 4
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    Structural analysis of vibroacoustical processes (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The method of automatic identification of acoustical signals, by means of the segmentation was used to investigate noises and vibrations in machines and mechanisms, for cybernetic diagnostics. The structural analysis consists of presentation of a noise or vibroacoustical signal as a sequence of segments, determined by the time quantization, in which each segment is characterized by specific spectral characteristics. The structural spectrum is plotted as a histogram of the segments, also as a relation of the probability density of appearance of a segment to the segment type. It is assumed that the conditions of ergodic processes are maintained.
    Keywords: STRUCTURAL MECHANICS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 179-180
    Format: text
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  • 5
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    Electronic strain-level counter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An electronic strain level counter for obtaining structural strain data on in-flight aircraft is described. The device counts the number of times the strain at a point on an aircraft structural member exceeds each of several preset levels. A dead band is provided at each level to prohibit the counting of small strain variations around a given preset level.
    Keywords: STRUCTURAL MECHANICS
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  • 6
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    Small, high pressure ratio compressor: Aerodynamic and mechanical design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Small, High-Pressure-Ratio Compressor Program was directed toward the analysis, design, and fabrication of a centrifugal compressor providing a 6:1 pressure ratio and an airflow rate of 2.0 pounds per second. The program consists of preliminary design, detailed areodynamic design, mechanical design, and mechanical acceptance tests. The preliminary design evaluate radial- and backward-curved blades, tandem bladed impellers, impeller-and diffuser-passage boundary-layer control, and vane, pipe, and multiple-stage diffusers. Based on this evaluation, a configuration was selected for detailed aerodynamic and mechanical design. Mechanical acceptance test was performed to demonstrate that mechanical design objectives of the research package were met.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-120941 , APS-5404-R-VOL-1
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  • 7
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    BUCLASP 3: A computer program for stresses and buckling of heated composite stiffened panels and other structures, user's manual (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of the computer program BUCLASP3 is described. The code is intended for thermal stress and instability analyses of structures such as unidirectionally stiffened panels. There are two types of instability analyses that can be effected by PAINT; (1) thermal buckling, and (2) buckling due to a specified inplane biaxial loading. Any structure that has a constant cross section in one direction, that may be idealized as an assemblage of beam elements and laminated flat and curved plate strip-elements can be analyzed. The two parallel ends of the panel must be simply supported, whereas arbitrary elastic boundary conditions may be imposed along any one or both external longitudinal side. Any variation in the temperature rise (from ambient) through the cross section of a panel is considered in the analyses but it must be assumed that in the longitudinal direction the temperature field is constant. Load distributions for the externally applied inplane biaxial loads are similar in nature to the permissible temperature field.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-112228
    Format: application/pdf
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  • 8
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    BUCLASP 2: A computer program for instability analysis of biaxially loaded composite stiffened panels and other structures (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of the computer program BUCLASP2 is described. The program is intended for linear instability analyses of structures such as unidirectionally stiffened panels. Any structure that has a constant cross section in one direction, that may be idealized as an assemblage of beam elements and laminated flat and curved plant strip elements can be analyzed. The loadings considered are combinations of axial compressive loads and in-plane transverse loads. The two parallel ends of the panel must be simply supported and arbitrary elastic boundary conditions may be imposed along any one or both external longitudinal side. This manual consists of instructions for use of the program with sample problems, including input and output information. The theoretical basis of BUCLASP2 and correlations of calculated results with known solutions, are presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-112226
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  • 9
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    Characterizations of four specimens processed as a part of the M553 sphere forming experiment performed during the Skylab 1 and 2 flight (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Four specimens identified as SL-1.3, SL-1.8, SL-1.9 and SL-2.5 were submitted for metallurgical characterization. These specimens had been processed in the M512 Facility as a part of the M553 Sphere Forming Experiment performed during the Skylab 1/2 flight. Three of these specimens, SL-1.3, SL-1.8, and SL-2.5 were designed to be melted completely by the electron beam and detach themselves from their support posts and resolidify while floating free in the near zero gravity and vacuum environment of space. Specimens SL-1.3 and SL-1.8 were completely melted, but it is believed they did not leave their posts before solidifying. Specimen SL-2.5 was only partially melted. Specimen SL-1.9 was to be completely melted and retained on a large sting which was accomplished as planned. The nominal composition of the four specimens was: (1) SL-1.3 - Ni 12% Sn; (2) SL-1.8 - Ni 30% Cu; (3) SL-1.9 - Pure Ni; and (4) SL-2.5 - Pure Ni. These four specimens have been examined according to the Phase B Characterization Plan. The results are discussed and compared with similar characterization analyses run on ground base specimens.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-129040
    Format: application/pdf
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  • 10
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    Characterization of nickel-copper alloy specimens processed as a part of the M553 sphere forming experiment during the Skylab 1 and 2 flight (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Both processed nickel-copper alloy specimens apparently completely melted by the electron beam in the Skylab M512 materials processing facility and either floated free in space, but collided with some smooth flat surface before solidifying, or remained attached to its support post during solidification. Both specimens had a smooth flat area on the surface due to this adherence during solidification. The nominal composition of the alloy before processing in space was 70 percent Ni and 30 percent Cu. Tests show that a considerable amount of copper was lost during processing by evaporation. It was further found that less copper was present in the cap areas, particularly at the surface, than was in the remainder of the specimens. The microchemistry of the dendrites and interdendritic regions, however, is in agreement with the phase diagram for this alloy. The measured densities of these specimens were less than the theoretical density of the alloy due to the amount of porosity present, however, no large voids were found by radiographic techniques.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-129039
    Format: application/pdf
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