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  • AIRCRAFT  (75)
  • STRUCTURAL MECHANICS  (72)
  • ASTROPHYSICS
  • 1970-1974  (110)
  • 1960-1964  (37)
  • 1972  (110)
  • 1963  (37)
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Keywords
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  • 1970-1974  (110)
  • 1960-1964  (37)
Year
  • 1
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    SOME CONSIDERATIONS OF THE PERFORMANCE OF A MANEUVERABLE, LIFTING-BODY, ENTRY VEHICLE (1963)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Heating and heat-shield requirements for maneuverable, lifting body, entry vehicle
    Keywords: STRUCTURAL MECHANICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    THE MISSION OF MARINER II- PRELIMINARY OBSERVATIONS (1963)
    In:  Other Sources
    Details
    Publication Date: 2019-05-11
    Description: Mariner ii space probe - preliminary observation
    Keywords: STRUCTURAL MECHANICS
    Type: JPL-TR-32-383
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A CRITICAL STUDY OF DELTA-WING CONFIGURATIONS FOR THE SUPERSONIC TRANSPORT APPLICATION (1963)
    In:  Other Sources
    Details
    Publication Date: 2019-05-11
    Description: Study of delta-wing configurations for supersonic transport application and their relation to aircraft performance
    Keywords: AIRCRAFT
    Type: IAS PAPER 63-5
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Residual strength and crack propagation tests on C-130 airplane center wings with service-imposed fatigue damage (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fourteen C-130 airplane center wings, each containing service-imposed fatigue damage resulting from 4000 to 13,000 accumulated flight hours, were tested to determine their fatigue crack propagation and static residual strength characteristics. Eight wings were subjected to a two-step constant amplitude fatigue test prior to static testing. Cracks up to 30 inches long were generated in these tests. Residual static strengths of these wings ranged from 56 to 87 percent of limit load. The remaining six wings containing cracks up to 4 inches long were statically tested as received from field service. Residual static strengths of these wings ranged from 98 to 117 percent of limit load. Damage-tolerant structural design features such as fastener holes, stringers, doublers around door cutouts, and spanwise panel splices proved to be effective in retarding crack propagation.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2075 , ER-11178
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Fixed base simulator study of an externally blown flap STOL transport airplane during approach and landing (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fixed-base simulator study was conducted to determine the flight characteristics of a representative STOL transport having a high wing and equipped with an external-flow jet flap in combination with four high-bypass-ratio fan-jet engines during the approach and landing. Real-time digital simulation techniques were used. The computer was programed with equations of motion for six degrees of freedom and the aerodynamic inputs were based on measured wind-tunnel data. A visual display of a STOL airport was provided for simulation of the flare and touchdown characteristics. The primary piloting task was an instrument approach to a breakout at a 200-ft ceiling with a visual landing.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6898 , L-8394
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Techniques in balloon X-ray astronomy. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Since the first balloon observation of the Crab Nebula balloon data have provided much information on the positions, spectra, time variability and pulsed nature of localized sources, and on the spectrum and isotropy of diffuse galactic and universal components. Measurements are limited to energies above about 20 keV by atmospheric attenuation at 2 to 3 g/sq cm depth and to below several hundred keV by detector sensitivity. Detectors usually consist of large-area Na I or Cs I scintillation counters with anticoincidence collimators for rejection of charged particles and scattered X-rays. Proportional counters are occasionally used at lower energies and solid-state detectors are used where extreme energy resolution is important. The instruments require a pointing capability on the order of 1.0 to 0.1 deg, depending on the collimator aperture. Digital data is either recorded on board or telemetered using a PCM technique.
    Keywords: AIRCRAFT
    Type: Space Science Reviews; 13; June 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Optimum mass-strength analysis for orthotropic ring-stiffened cylinders under axial compression (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis was developed to calculate the minimum mass-strength curve for an orthotropic cylinder subjected to axial compressive loading. The analysis, which includes the effects of ring and stringer eccentricities, is in a general form so that various cylinder wall and stiffener geometries can be considered. Several different ring-stiffened orthotropic configurations were studied. The minimum mass-strength curves and the dimensions associated with these curves are presented for (in order of decreasing efficiency) a tubular double bead, a nonsymmetric double bead, a Z-stiffened skin, and a trapezoidal corrugation. A comparison of efficiencies of the configurations shows a tubular element cylinder to be more efficient than a 3-percent core-density honeycomb-sandwich cylinder. It was found that for an optimized Z-stiffened skin, the location of the Z-stiffeners (internal or external) made a negligible difference in efficiency.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6772 , L-7060
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Analysis of the transient response of shell structures by numerical methods. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper examines some basic considerations underlying dynamic shell response analysis and the impact of these considerations upon the practical aspects of solution by numerical methods. Emphasis is placed on the solution of linear problems. The present states of development of the finite difference and finite element methods are reviewed, and techniques for the treatment of temporal variation are discussed. An examination is made of the frequency parameters characteristic of thin shell theory, applied excitations, and spatial mesh geometries, and the significance of these parameters with respect to computational convergence is illustrated.
    Keywords: STRUCTURAL MECHANICS
    Type: Dynamic response of structures; Symposium; Jun 28, 1971 - Jun 29, 1971; Stanford, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Automated procedures for sizing aerospace vehicle structures /SAVES/ (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results from a continuing effort to develop automated methods for structural design are described. A system of computer programs presently under development called SAVES is intended to automate the preliminary structural design of a complete aerospace vehicle. Each step in the automated design process of the SAVES system of programs is discussed, with emphasis placed on use of automated routines for generation of finite-element models. The versatility of these routines is demonstrated by structural models generated for a space shuttle orbiter, an advanced technology transport,n hydrogen fueled Mach 3 transport. Illustrative numerical results are presented for the Mach 3 transport wing.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 72-332 , Structures, Structural Dynamics, and Materials Conference; Apr 10, 1972 - Apr 12, 1972; San Antonio, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Study of Load Alleviation and Mode Suppression (LAMS) on the YF-12A airplane (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The potentials and capability for implementing a LAMS (load alleviation and mode suppression) system on the YF-12A for the purpose of flight research were evaluated. The nature of the research is to minimize the design risk in application of LAMS to future aircraft. The results of the study show that the YF-12A would be a suitable test bed for continuing development of LAMS technology. This was demonstrated by defining five candidate LAMS systems and analytically evaluating them with regard to performance and mechanization. Each of the five systems used a different combination of force producers. A small canard vane or a mass-reaction device mounted near the cockpit was considered as a possible LAMS force producer, together with the existing inboard and outboard elevons. It was concluded that a combination of canard vane and outboard elevons would provide the most effective system for the YF-12A.
    Keywords: AIRCRAFT
    Type: NASA-CR-2158
    Format: application/pdf
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