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  • STRUCTURAL MECHANICS  (57)
  • AIRCRAFT  (53)
  • ASTROPHYSICS
  • 1970-1974  (110)
  • 1960-1964
  • 1972  (110)
Collection
Keywords
Years
  • 1970-1974  (110)
  • 1960-1964
Year
  • 1
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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
  • 2
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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
  • 3
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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
  • 4
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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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  • 5
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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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  • 6
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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
  • 7
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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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  • 8
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    A fracture mechanics analysis of adhesive failure in a single lap shear joint. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Discussion of adhesive fracture of single lap shear joints in terms of a maximum stress criterion and an energy balance. The Goland and Reissner (1944) analysis is used to determine the stress distribution in the adhesive assembly, and the results obtained are introduced into an energy balance to determine the initiation of adhesive fracture. In the stress analysis the loads at the edges of the joint are first determined. This is a problem in which the deformation of the joint sheets must be taken into account and is solved by using the finite-deflection theory of cylindrically bent plates. Then the stress in the joint due to applied loads is determined. This problem is formulated as one in plane strain consisting of two rectangular sheets of equal thickness and unit width. With the aid of this stress analysis and the stresses obtained from the conditions of equilibrium the contributions to the energy change with crack length are calculated. The analysis performed is then compared with a maximum stress criterion for a lap joint.
    Keywords: STRUCTURAL MECHANICS
    Type: SESA PAPER 1990A , Society for Experimental Stress Analysis, Spring Meeting; May 23, 1972 - May 26, 1972; Cleveland, OH
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Flap noise (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Externally-blown-flap noise research can be summarized by the following remarks: With lower-surface blowing, the sources of the flap noise are begining to be understood and the noise scaling laws have been established. Further, progress has been made on suppressing the flap interaction noise at the large flap deflections used during landing. Recent small-scale noise tests of configurations using external upper-surface blowing indicate that engine-over-the-wing configurations may be promising.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 259-290
    Format: text
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  • 10
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    Quiet engine design highlights (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Three high performance fans were designed, built, and tested, accumulating 444 hours. All three fans are both aerodynamically and mechanically suitable for direct incorporation into engine applications. Two turbofan demonstrators to evaluate both low- and high-speed fan systems were also designed, built, and tested. All components and engine systems are demonstrating high reliability. These components have demonstrated advanced state-of-the-art in acoustics, aerodynamics, and mechanical design.
    Keywords: AIRCRAFT
    Type: NASA. Lewis Res. Center Aircraft Engine Noise Reduction; p 143-162
    Format: text
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