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  • PROPULSION SYSTEMS  (52)
  • STRUCTURAL MECHANICS  (46)
  • FLUID MECHANICS
  • ASTROPHYSICS
  • 1990-1994
  • 1970-1974  (130)
  • 1960-1964
  • 1973  (130)
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  • 1990-1994
  • 1970-1974  (130)
  • 1960-1964
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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
    Publikationsdatum: 2019-06-27
    Beschreibung: 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 .
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: 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
    Publikationsdatum: 2019-06-27
    Beschreibung: 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
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: NASA-CR-132299
    Format: application/pdf
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  • 3
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    Optimal low thrust geocentric transfer (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A computer code which will rapidly calculate time-optimal low thrust transfers is being developed as a mission analysis tool. The final program will apply to NEP or SEP missions and will include a variety of environmental effects. The current program assumes constant acceleration. The oblateness effect and shadowing may be included. Detailed state and costate equations are given for the thrust effect, oblateness effect, and shadowing. A simple but adequate model yields analytical formulas for power degradation due to the Van Allen radiation belts for SEP missions. The program avoids the classical singularities by the use of equinoctial orbital elements. Kryloff-Bogoliuboff averaging is used to facilitate rapid calculation. Results for selected cases using the current program are given.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIAA PAPER 73-1074 , Electric Propulsion Conference; Oct 31, 1973 - Nov 02, 1973; Lake Tahoe, NV
    Format: text
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  • 4
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    Structural analysis of vibroacoustical processes (1973)
    In:  CASI
    Details
    Publikationsdatum: 2006-03-28
    Beschreibung: 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.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: 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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    Development of propulsion for high atmospheric pressure or dense environments (1973)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-22
    Beschreibung: The development of a propulsion system that employs a detonating propellant is described, and the need for such a system and its use in certain planetary atmospheres are demonstrated. A theoretical formulation of the relevant gas-dynamic processes was developed, and a related series of experimental tests were pursued.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-52
    Format: text
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  • 6
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    A computer program to calculate radiating viscous stagnation streamline flow with strong blowing (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A computer program (program LEE) has been developed to calculate the fully coupled solution of the radiating viscous stagnation streamline flow with strong blowing. The report describes the digital computer program, including FORTRAN IV listing, flow charts, instructions for the user, and a test case with input and output. Program LEE is available through COSMIC.
    Schlagwort(e): FLUID MECHANICS
    Materialart: NASA-TM-X-2805 , L-8918
    Format: application/pdf
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  • 7
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    Analysis of free turbulent shear flows by numerical methods (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Studies are described in which the effort was essentially directed to classes of problems where the phenomenologically interpreted effective transport coefficients could be absorbed by, and subsequently extracted from (by comparison with experimental data), appropriate coordinate transformations. The transformed system of differential equations could then be solved without further specifications or assumptions by numerical integration procedures. An attempt was made to delineate different regimes for which specific eddy viscosity models could be formulated. In particular, this would account for the carryover of turbulence from attached boundary layers, the transitory adjustment, and the asymptotic behavior of initially disturbed mixing regions. Such models were subsequently used in seeking solutions for the prescribed two-dimensional test cases, yielding a better insight into overall aspects of the exchange mechanisms.
    Schlagwort(e): FLUID MECHANICS
    Materialart: NASA. Langley Res. Center Free Turbulent Shear Flows, Vol. 1; p 185-232
    Format: application/pdf
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  • 8
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    Electronic strain-level counter (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): STRUCTURAL MECHANICS
    Format: application/pdf
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  • 9
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    Impact resistance of fiber composite blades used in aircraft turbine engines (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Resistance of advanced fiber reinforced epoxy matrix composite materials to ballistic impact was investigated as a function of impacting projectile characteristics, and composite material properties. Ballistic impact damage due to normal impacts, was classified as transverse (stress wave delamination and splitting), penetrative, or structural (gross failure). Steel projectiles were found to be gelatin ice projectiles in causing penetrative damage leading to reduced tensile strength. Gelatin and ice projectiles caused either transverse or structural damage, depending upon projectile mass and velocity. Improved composite transverse tensile strength, use of dispersed ply lay-ups, and inclusion of PRD-49-1 or S-glass fibers correlated with improved resistance of composite materials to transverse damage. In non-normal impacts against simulated blade shapes, the normal velocity component of the impact was used to correlate damage results with normal impact results. Stiffening the leading edge of simulated blade specimens led to reduced ballistic damage, while addition of a metallic leading edge provided nearly complete protection against 0.64 cm diameter steel, and 1.27 cm diameter ice and gelatin projectiles, and partial protection against 2.54 cm diameter projectiles of ice and gelatin.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-134502 , PWA-4727
    Format: application/pdf
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  • 10
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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
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: NASA-CR-112228
    Format: application/pdf
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