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  • Other Sources  (84)
  • STRUCTURAL MECHANICS  (45)
  • MACHINE ELEMENTS AND PROCESSES  (39)
  • 1970-1974  (84)
  • 1965-1969
  • 1950-1954
  • 1935-1939
  • 1972  (84)
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  • Other Sources  (84)
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  • 1970-1974  (84)
  • 1965-1969
  • 1950-1954
  • 1935-1939
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  • 1
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    A non-linear dynamic lumped-parameter model of a rectangular plate. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A lumped-parameter model of a rectangular plate is developed by assuming fundamental mode solutions and using Hamilton's Principle and the Euler equations to set up the differential equation of motion for the system. The plate theory used may be described as the dynamic analogue of the von Karman large-deflection theory. Four sets of symmetrical boundary conditions are considered with the restriction of uniform pressure dynamic loads. The model takes the form of a mass on a cubic-hardening spring with each term defined by algebraic expressions of the plate parameters. The results for some specific problems are compared with two previous solutions. This method is less accurate but simpler to develop and apply.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Sound and Vibration; 21; Apr. 8
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A comparison of the capabilities of three finite element programs (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Three finite element programs are compared to assess their capabilities as an analysis tool in a structural design process. Because of the need for repetitive analyses as an integral part of a design loop, a candidate program must be capable of handling large problems, operate efficiently, and be readily adaptable for use in computer-aided design. The three programs considered in the study, ELAS,SNAP, and NASTRAN, range from a relatively small finite element program limited to static structural analysis (ELAS) to a large complex general analysis system (NASTRAN). Results are given for comparative speeds and computer resources required for each program in the analysis of sample fuselage problems representative of practical aircraft design.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 277-287
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Experiences in interfacing NASTRAN with another finite element program (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The coupling of NASTRAN to another finite element program developed for the static analysis of automotive structures is discussed. The two programs were coupled together to use the substructuring capability of the in-house program and the normal mode analysis capability of NASTRAN. Modifications were made to the NASTRAN program in order to make the coupling feasible.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 111-119
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Coupling between structure and liquids in a parallel stage space shuttle design (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was conducted to determine the influence of liquid propellants on the dynamic loads for space shuttle vehicles. A parallel-stage configuration model was designed and tested to determine the influence of liquid propellants on coupled natural modes. A forty degree-of-freedom analytical model was also developed for predicting these modes. Currently available analytical models were used to represent the liquid contributions, even though coupled longitudinal and lateral motions are present in such a complex structure. Agreement between the results was found in the lower few modes.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-127631 , AIAA PAPER 72-347-REV
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    User's manual for the Simulated Life Analysis of Vehicle Elements (SLAVE) model (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The simulated life analysis of vehicle elements model was designed to perform statistical simulation studies for any constant loss rate. The outputs of the model consist of the total number of stages required, stages successfully completing their lifetime, and average stage flight life. This report contains a complete description of the model. Users' instructions and interpretation of input and output data are presented such that a user with little or no prior programming knowledge can successfully implement the program.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-123642 , ASD-ASTN-1519
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Performance of 40-millimeter-bore ball bearings with lead- and lead-alloy-plated retainers in liquid hydrogen at 1.2 million DN (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Forty-millimeter-bore ball bearings with lead- and lead-alloy-coated retainers were operated in liquid hydrogen at 30,000 rpm under a thrust load of 1780 N (400 lb.) Four different substrate materials were used for the retainer. Longer bearing run times were achieved with a lead-tin-copper alloy coating plated onto a leaded-bronze material (22.5 hr) and an aluminum-bronze alloy (19.3 hr). One bearing with a pure lead coating achieved the desired objective of 10 hr. This bearing had an aluminum - bronze substrate retainer and ran successfully for 12.4 hr. Additions of antimony to the lead provided an alloy coating with better wear resistance than pure lead; however, this coating was abrasive to the outer-race lands.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-TN-D-6981 , E-6916
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Summary of nondestructive testing theory and practice (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The ability to fabricate design critical and man-rated aerospace structures using materials near the limits of their capabilities requires a comprehensive and dependable assurance program. The quality assurance program must rely heavily on nondestructive testing methods for thorough inspection to assess properties and quality of hardware items. A survey of nondestructive testing methods is presented to provide space program managers, supervisors and engineers who are unfamiliar with this technical area with appropriate insight into the commonly accepted nondestructive testing methods available, their interrelationships, used, advantages and limitations. Primary emphasis is placed on the most common methods: liquid penetrant, magnetic particle, radiography, ultrasonics and eddy current. A number of the newer test techniques including thermal, acoustic emission, holography, microwaves, eddy-sonic and exo-electron emission, which are beginning to be used in applications of interest to NASA, are also discussed briefly.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-2120 , BMI-NLVP-TM-71-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Multimaterial lamination as a means of retarding penetration and spallation failures in plates (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental data are presented which show that hypervelocity impact spallation and penetration failures of a single solid aluminum plate and of a solid aluminum plate spaced a distance behind a Whipple meteor bumper may be retarded by replacing the solid aluminum plate with a laminated plate. Four sets of experiments were conducted. The first set of experiments was conducted with projectile mass and velocity held constant and with polycarbonate cylinders impacted into single plates of different construction. The second set of experiments was done with single plates of various construction and aluminum spherical projectiles of similar mass but different velocities. These two experiments showed that a laminated plate of aluminum and polycarbonate or aluminum and methyl methacrylate could prevent spallation and penetration failures with a lower areal density than either an all-aluminum laminated plate or a solid aluminum plate. The aluminum laminated plate was in turn superior to the solid aluminum plate in resisting spallation and penetration failures. In addition, through an example of 6061-T6 aluminum and methyl methacrylate, it is shown that a laminated structure ballistically superior to its parent materials may be built. The last two sets of experiments were conducted using bumper-protected main walls of solid aluminum and of laminated aluminum and polycarbonate. Again, under hypervelocity impact conditions, the laminated main walls were superior to the solid aluminum main walls in retarding spallation and penetration failures.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6989 , L-8444
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Performance of high speed ball bearings with lead plated retainers in liquid hydrogen for potential use in a radiation environment (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Ball bearings (40-mm bore) with lead coated, aluminum-bronze retainers were operated successfully in liquid hydrogen at 30,000 rpm under a thrust load of 1780 newtons (400 lb) for running times up to 15 hours. The lead transfer films on the bearing surfaces prevented galling of bearing components. The lead coated retainers used in this investigation show promise for use in the high radiation environments, where polytetrafluoroethylene (PTFE) based materials are not suitable. Failure was a result of the loss of lead lubricant on the retainer-inner-land and ball-pocket surfaces. The longest bearing life (15 hr) was achieved with a lead coating thickness of 50 micrometers (0.002 in.) on the retainer. Other bearings had lives of 2 to 6 hours.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-TN-D-6653 , E-6642
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Fatigue flaw growth and NDI evaluation for preventing through cracks in spacecraft tankage structures (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program was conducted to determine the fatigue-crack propagation behavior of parent and welded 2219-T87 aluminum alloy sheet under controlled cyclic stress conditions in room temperature air and 300 F air. Specimens possessing an initial surface defect of controlled dimensions were cycled under constant load amplitude until the propagating fatigue crack penetrated the back surface of the specimen. A series of precracked specimens were prepared to determine optimum penetrant, X-ray, ultrasonic, and eddy current nondestructive inspection procedures.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-128600 , LR-25387
    Format: application/pdf
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