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  • STRUCTURAL MECHANICS  (281)
  • AERODYNAMICS
  • 1970-1974  (533)
  • 1925-1929
  • 1972  (533)
Collection
Keywords
Years
  • 1970-1974  (533)
  • 1925-1929
Year
  • 1
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    Assessment of advances in structural analysis for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The latest technology for structural analysis in relation to the design tasks that lie ahead for the space shuttle is reviewed. For shell-of-revolution structures, the analysis can be formulated as a one-dimensional problem which is readily solved by using finite-difference or numerical-integration techniques. For more general asymmetric shells, a two-dimensional formulation is required. However, the governing equations are readily formulated and are amenable to solution by finite-difference techniques. For a completely general structural arrangement, such as structural frameworks, recourse is usually made to discretized formulations using finite elements. Of course, the finite-element programs could be used for shell structures, but at a loss in accuracy and increase in computer time compared with the special purpose programs.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA Space Shuttle Technol. Conf.; p 685-725
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  • 2
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    In-flight aeroacoustic environments on prospective space shuttle vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The problem of in-flight aerodynamic noise has been studied by reliable estimates of full scale surface-pressure fluctuations from scale model tests in wind tunnels. Scaling relationships have been verified, and many details of the fluctuating pressure characteristics such as spatial correlation and convection velocities are understood. The effects of the wind tunnel environmental turbulence and noise have also been investigated sufficiently so that threshold levels of usable data are known.
    Keywords: AERODYNAMICS
    Type: NASA Space Shuttle Technol. Conf.; p 71-96
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  • 3
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    Summary and future plans (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 121-133
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  • 4
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    Piloting and operational aspets of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 97-110
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  • 5
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    Status of the F-8 supercritical wing program (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 49-58
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  • 6
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    F-8 supercritical wing pressure distribution evaluation (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 71-84
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  • 7
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    Buffet characteristics of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 85-96
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  • 8
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    The NASA supercritical airfoil and its application to swept wings (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 1-12
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  • 9
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    Evolution of the F-8 supercritical wing configuration (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 35-48
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  • 10
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    EBF noise tests with engine under-the-wing and over-the-wing configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Noise tests of externally blown flaps with the engine under the wing and engine over the wing configurations were conducted. Flap noise data obtained on a TF-34 aircraft are discussed. Noise data obtained during a free-jet forward-speed-effect analysis are presented. Noise sources associated with upper surface flap blowing are described. Results of a small scale configuration screening study and some large scale model test data are analyzed. The noise data for the engine over wing configurations are compared with the engine under the wing configurations.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 455-473
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  • 11
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    Flap noise generation and control (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The characteristics of aerodynamic noise generated by the interaction of an airstream with a flap surface are discussed. The location and behavior of various noise sources were investigated to determine optimal quieting techniques. A schematic diagram of the jet-flap concepts being considered for integrated-powered-lift systems for short takeoff aircraft is shown. Each of the concepts has in common high velocity turbulent air flowing over relatively rigid surfaces with resultant production of interaction noise. The nature, location, and control of noise sources which involve the interactions of air flows with airfoil surfaces are examined.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 413-426
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  • 12
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    Acoustic characteristics of large-scale STOL models at forward speed (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmentor wing model was equipped with an unlined augmentor blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 443-454
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  • 13
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    Externally blown flap impingement noise (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Tests of the noise produced by the impingement of the jet exhaust on the wing and flap for an externally blown flap system were conducted with a CF700 turbofan engine and an F-111B wing panel. The noise produced with a daisy nozzle installed on the engine was greater than that produced by a conical nozzle at the same thrust. The presence of the wing next to the test nozzles increased the noise, as did increasing the flap deflection angle. Compared with the conical nozzle, the daisy nozzle produced slightly less noise at a flap deflection of 60 deg but produced more noise at the lower flap deflections tested. Tests showed that the single-slotted flap deflected 60 deg, produced less noise than the double-slotted flaps. Also, maintaining the maximum distance between the exit nozzle and flap system resulted in a minor reduction in noise.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 427-441
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  • 14
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    Survey of wing and flap lower-surface temperatures and pressures during full-scale ground tests of an externally blown flap system (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Full-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing, vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power and engine/wing positions. The tests were made with no airflow over the wing. The leading-edge wing sweep angle was fixed at 26 deg, the angle of incidence between the engine and the wing was fixed at 3 deg, and the tests were conducted with the flap retracted, extended and deflected 35 deg, and extended and deflected 60 deg. The integrated local pressures on the undersurface of the flap produced loads approximately three times as great at the 60 deg flap position as at the 35 deg flap position. With both nozzle configurations, more than 90 percent of the integrated pressure loads were contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline. The maximum temperature recorded on the flaps was 218 C (424 F) for the conical nozzle and 180 C (356 F) for the daisy nozzle.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 143-156
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  • 15
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    Simulator evaluation of the flying qualities of externally blown flap and augmentor wing transport configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap configuration or an augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display, (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of-freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 157-800
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  • 16
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    Aerodynamics of the upper surface blow flap (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The results of some preliminary wind-tunnel investigations made to provide fundamental aerodynamic information on the upper surface blown jet-flap concept incorporating high-bypass-ratio turbofan engines are summarized. The results of the investigation have shown the concept to have aerodynamic performance generally similar to that of other externally blown high-lift systems. A few of the more critical problems associated with this concept have been identified and preliminary solutions to some of these problems have been found. These results have proven to be sufficiently encouraging to warrant continuation of fundamental research efforts on the concept.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center STOL Technol.; p 97-110
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  • 17
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    Advanced augmentor-wing research (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Results of research on advanced augmentors are discussed. Research concerned with performance has indicated that: (1) augmentors with lobe-type nozzles give higher thrust augmentation than those with slot-type primary nozzles, (2) the thrust of augmentor wings at forward speed is greater than that of internally blown flaps for the speed range of interest, and (3) the optimum augmentor geometry at forward speed may be different from the optimum static geometry. Analysis of augmentor-wing data has shown that the data may be correlated by accounting for the augmentation and entrainment in defining a net thrust coefficient.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 87-96
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  • 18
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    Aerodynamic characteristics of a swept augmentor wing (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: A brief outline of augmentor wing research sponsored by Ames Research Center is presented and is followed by a discussion of large-scale wind-tunnel test results for a swept augmentor wing configuration. The results showed that the augmentor wing could be applied to high-speed swept wing designs with little adverse effect on either the basic performance of the augmentor or the longitudinal characteristics, including maximum lift and stall. Three lateral control devices were shown to be effective and ground effect was measured for several complete aircraft configurations.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 71-86
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  • 19
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    Aerodynamic loads measurements on externally blown flap STOL models (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Small-scale-model data have shown large static loads on the flap system behind the engines. The large-scale-model tests confirmed the magnitude of these loads and indicated that the relative loading of each flap element depends on the engine-wing-flap geometry. Flap response measurements indicated that the unsteady pressure loading excited the natural vibration modes of the flap system on this model. Since this was a boilerplate model, the only conclusion that can be drawn is that the possibility of large vibration loads must be considered for a flight-weight structure. The similarity of the unsteady pressure and flap response spectra for the wind-off and wind-on cases indicated that it may be possible to realistically test flight-weight flap structures on a static test stand rather than endure the extra costs and scheduling problems associated with large-scale wind-tunnel tests. There is a potential flap-temperature problem which if not resolved might preclude the use of materials such as aluminum and the composites in the flap structure.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 121-130
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  • 20
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    Aerodynamic and performance characteristics of externally blown flap configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The application of externally blown flaps for improving the performance of short takeoff aircraft is discussed. The characteristics of externally blown flap powered lift are examined. A method for predicting the aerodynamic performance of a particular externally blown flap configuration is presented. The following specific effects are analyzed: (1) induced aerodynamics, (2) static turning, (3) flap span and deflection, and (4) engine size and chord flap.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 43-54
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  • 21
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    Stability and control of externally blown flap configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The results of wind-tunnel investigations on the stability and control characteristics of externally blown jet-flap configurations are presented. Conventional wind-tunnel tests and free-flight model tests have shown that longitudinal trim and stability can be achieved by a properly located horizontal tail of sufficient size, and that lateral trim in the engine-out condition can be produced by combinations of differential flap, spoiler, and rudder deflection. Free-flight model tests have revealed a lightly damped Dutch roll lateral oscillation, and have shown that the oscillation can be stabilized by use of artificial damping.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 55-70
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  • 22
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    Reduction of wave drag by antisymmetric arrangement of wings and bodies. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The wave interference effects for bodies or wings in a mirror-symmetric arrangement, and in an antisymmetric arrangement are discussed. It is shown that while in the case of a mirror-symmetric arrangement large adverse interference effects can be observed, antisymmetric arrangements provide comparatively much smaller wave drags. The single continuous wing panels also adapt themselves more readily to varying angles of obliquity, and hence, to varying flight speeds. A detailed review is presented of the previous work on the aerodynamic properties and flight stability of oblique elliptic wing combinations. A possible mode of application of these combinations to transport aircraft operating at moderate supersonic speeds is suggested.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Feb. 197
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  • 23
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    Impact probe displacement in a supersonic turbulent boundary layer. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The experiment was performed on the test section sidewall in a supersonic pressure tunnel. The boundary layer at the test station was surveyed in turn by each of 8 impact probes ranging in size from about 1.3 to 48 mm. The impact pressures measured by these probes were combined with the test section static pressure to calculate Mach numbers. Probe displacement effects were evaluated in terms of these Mach number values.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Apr. 197
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  • 24
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    Effects of transverse outflow from a hypersonic separated region. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Features of hypersonic, finite-span separated flows with a turbulent boundary layer have been studied to provide a partial assessment of transverse outflow effects on separated flowfield characteristics. Results demonstrate the critical importance of transverse outflow in determining some of the characteristic features of a turbulent, separated boundary layer.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Apr. 197
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  • 25
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    Finite elements of nonlinear continua. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The finite element method is extended to a broad class of practical nonlinear problems, treating both theory and applications from a general and unifying point of view. The thermomechanical principles of continuous media and the properties of the finite element method are outlined, and are brought together to produce discrete physical models of nonlinear continua. The mathematical properties of the models are analyzed, and the numerical solution of the equations governing the discrete models is examined. The application of the models to nonlinear problems in finite elasticity, viscoelasticity, heat conduction, and thermoviscoelasticity is discussed. Other specific topics include the topological properties of finite element models, applications to linear and nonlinear boundary value problems, convergence, continuum thermodynamics, finite elasticity, solutions to nonlinear partial differential equations, and discrete models of the nonlinear thermomechanical behavior of dissipative media.
    Keywords: STRUCTURAL MECHANICS
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  • 26
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    Dynamic response analysis of geometrically non-linear structures subjected to high impact. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Description of an efficient digital computer method for the determination of the propagation of elastic stresses and deformations in certain geometrically nonlinear structures subjected to high impact loading. The finite-element matrix displacement approach utilizing curved quadrilateral shell elements in conjunction with a nodewise predictor-corrector method employing Runge-Kutta extrapolation techniques has been adopted for the present solution. The related computer program written in FORTRAN V for the UNIVAC 1108 computer has proved to be effective for the solution of a range of practical problems including rectangular and cylindrical panels. Numerical results are presented for a relevant structure, the cell container, and the negative electrode of an impact-resistant battery subjected to high impact, simulating its free landing on a planetary surface.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal for Numerical Methods in Engineering; 4; Mar
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  • 27
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    Buckling of nearly cylindrical shells under lateral pressure. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The effect of slight meridional curvature on the buckling of shells subjected to an external constant directional lateral pressure is examined. A class of nearly cylindrical shells with constant meridional curvature, a central radius-to-thickness ratio of 500, and central rise-to-shell-length ratios varying from plus 5% to minus 5% is considered. A brief study is presented of the dependence of the critical lateral pressure on the meridional curvature and on the length and meridional edge restraint.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Feb. 197
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  • 28
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    Effect of a slot on the buckling load of a cylindrical shell with a circular cutout. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The results are discussed of a study of the effect of slots on the buckling of cylinders with circular holes of systematically varied circularity. The results obtained suggest that the substantial increase in the buckling loads of cylindrical shells resulting from increases in slot length is due to a relief of the bending stress field.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Feb. 197
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  • 29
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    Turbulent-wake calculations with an eddy-viscosity model. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A simple eddy-viscosity model is shown to make it possible to calculate numerically the mean properties of a turbulent wake. Although the structure of the Reynolds stress terms is not resolved, the results obtained are adequate for predicting velocity profiles and displacement thicknesses.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Feb. 197
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  • 30
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    Experimental investigation of strains in fabric under biaxial and shear forces. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The paper defines the experimental phase of an objective to obtain the mechanical characteristics and coefficients required by the generalized form of Hooke's law for nylon-polyurethane-coated fabric. Test specimens were cylindrical fabric sleeves and were loaded in axial tension by an Instron, in hoop tension by pressurizing, and in shear by a torquing fixture. An extensive amount of strain data is included for a wide combination of the three membrane loads. The tests indicate highly nonlinear stress-strain characteristics of the fabric and a strong dependency on all three membrane loads.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft; 9; Jan. 197
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  • 31
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    Shock-wave, turbulent boundary-layer interaction on a blunted compression surface. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The application of Rose's (1970) analytical method to the study of a shock wave interacting with a turbulent layer on a blunted compression surface is described. Only those details of the method that specifically apply to the case under consideration are discussed.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Apr. 197
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  • 32
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    Sonic-boom-induced building structure responses including damage. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Concepts of sonic-boom pressure loading of building structures and the associated responses are reviewed, and results of pertinent theoretical and experimental research programs are summarized. The significance of sonic-boom load time histories, including waveshape effects, are illustrated with the aid of simple structural elements such as beams and plates. Also included are discussions of the significance of such other phenomena as three-dimensional loading effects, air cavity coupling, multimodal responses, and structural nonlinearities. Measured deflection, acceleration, and strain data from laboratory models and full-scale building tests are summarized, and these data are compared, where possible, with predicted values. Damage complaint and claim experience due both to controlled and uncontrolled supersonic flights over communities are summarized with particular reference to residential, commercial, and historic buildings. Sonic-boom-induced building responses are compared with those from other impulsive loadings due to natural and cultural events and from laboratory simulation tests.
    Keywords: STRUCTURAL MECHANICS
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  • 33
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    Establishing an upper bound for window response to the sonic boom. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Study of the failure of glass windows, which is probably the most severe problem confronting the SST program outside of the psychological and sociological aspects. The structural configuration most likely to suffer a window failure due to sonic boom excitation is one representable by a single large room, a single large window, and an open door. It is suggested that if the open door were replaced with another window the resultant stresses in both windows would be substantially reduced.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Sound and Vibration; 21; Mar. 22
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  • 34
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    Measurements of skin friction on the wall of a hypersonic nozzle. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Direct skin friction measurements obtained on the wall of a Mach 19.8 nozzle are presented. These measurements of skin friction and values deduced from the profile data are compared with predictions from a finite difference theory and also with several 'flat-plate' prediction methods for skin friction.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Sept
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  • 35
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    Plane elastostatic analysis of V-notched plates. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Solutions are given for several plane elastostatic problems of plates having a V-notch on one edge, and subjected to a variety of boundary conditions. The effect of the magnitude of the V-notch angle and specimen geometry on stress intensity factors KI and KII are obtained for unloaded notch surfaces. There is less than one per cent difference in opening model stress intensity factor in going from a zero degree notch angle to a 30 degree notch angle. Notch opening displacements at the plate edge were measured experimentally, and the results obtained were in excellent agreement with the computed results.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal of Fracture Mechanics; 8; Sept
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  • 36
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    Taylor instability in the shock layer on a Jovian atmosphere entry probe. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Investigation of the Taylor instability relative to the dynamical instability whose presence in the shock layer on a spacecraft entering the Jovian atmosphere is to be expected because of the difference in velocity across the shear layer. Presented calculations show that the Taylor instability at the interface between shock-heated freestream gas and ablation products is inconsequential in comparison to the shear layer instability.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Sept
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  • 37
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    Transition in compressible free shear layers. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The transition Reynolds number for shear layers produced by interactions between weak and strong shock waves is determined on the basis of experiments performed in a 20-in. (Mach 6) and an 11-in. (Mach 6.9) hypersonic tunnel. A variable angle wedge was used to generate a planar shock wave which interacted with the bow wave of a blunt body. An average value of the transition length (defined as the length along the shear layer from the shock interaction to the point where turbulence became visible on schlieren photographs) was used to determine the transition Reynolds number.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Aug. 197
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  • 38
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    Correlations of peak heating in shock interference regions at hypersonic speeds. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Correlations are given of measured pressure and heat-transfer peaks for shock/boundary-layer interactions and shear layer attachment on configurations with both two- and three-dimensional interactions. The peak values were obtained from an investigation of shock interference heating on hemispheres, a 30-deg included angle wedge, and a 2.54-cm-diam cylindrical leading-edge fin model. The investigation covers data for Mach numbers of 6 and 20 over freestream Reynolds numbers ranging from (3.3 to 25.6) million per meter, and specific heat ratios of 1.4 and 1.67.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Aug. 197
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  • 39
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    Study of fatigue crack initiation from flaws using fracture mechanics theory. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: STRUCTURAL MECHANICS
    Type: Engineering Fracture Mechanics; 4; June 197
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  • 40
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    The effect of angle of attack on boundary-layer transition on cones. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Boundary-layer transition on 5- and 15-deg half-angle cones was studied as a function of angle of attack (ranging from 0 to 20 deg) in a 3.5 ft hypersonic wind tunnel at a freestream Mach number of 7.4. It is shown that the influence of the angle of attack on the transition Reynolds number is a function of the meridian angle. On the windward ray of the 15-deg cone, transition Reynolds numbers show an initial slight increase and then a decrease with increasing angle of attack; leeward-ray Reynolds numbers for this cone decrease rapidly with angle of attack. Windward-ray transition Reynolds numbers increase monotonically with angle of attack on the 5-deg cone, but the effect of the angle of attack on the leeward ray is the same as for the 15-deg cone.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Aug. 197
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  • 41
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    Panel-flutter analysis of a thermal protection-shield concept for the space shuttle. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Analysis of the panel flutter characteristics of a candidate thermal protection system (TPS) for the space shuttle, using piston theory aerodynamics and Lagrange equations. The results show the TPS candidate panel array to be deep in the 'no-flutter' region during launch and, therefore, safe from panel flutter.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Aug. 197
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  • 42
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    Rayleigh wave effects in an elastic half-space. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Consideration of Rayleigh wave effects in a homogeneous isotropic linearly elastic half-space subject to an impulsive uniform disk pressure loading. An approximate formula is obtained for the Rayleigh wave effects. It is shown that the Rayleigh waves near the center of loading arise from the portion of the dilatational and shear waves moving toward the axis, after they originate at the edge of the load disk. A study is made of the vertical displacement due to Rayleigh waves at points on the axis near the surface of the elastic half-space.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Aug. 197
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  • 43
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    Strongly coupled stress waves in heterogeneous plates. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Consideration of coupled stress waves generated by an impulsive load applied at one end of a semiinfinite plate. For the field equations governing the one-dimensional coupled waves a hyperbolic system of equations is obtained in which a strong coupling in the second derivatives exists. The method of characteristics described by Chou and Mortimer (1967) is extended to cover the case of strong coupling, and a study is made of the transient stress waves in a semiinfinite plate subjected to an initial step input. Coupled discontinuity fronts are found to propagate at different velocities. The normal plate stress and the bending moment at different time regimes are illustrated by graphs.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Aug. 197
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  • 44
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    Computation of transonic flow about finite lifting wings. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The results of Murman and Krupp (1971) are used to develop a procedure for computing a transonic flow about a finite lifting wing. A small disturbance equation describing the velocity potential of three-dimensional wings is solved in the process. The procedure is applied to a wing with a symmetric biconvex airfoil section in a zero-incidence subsonic flow, to a supersonic rectangular lifting wing with a sharp leading edge and to a subcritical nonlifting rectangular wing with a blunt leading edge.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; July 197
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  • 45
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    Subsonic, transonic, and supersonic nozzle flow by the inverse technique. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The inverse technique is used to obtain a mathematically and physically consistent solution of the flowfield in a nozzle from the mass generation surface through the supersonic region. The inverse method employs an assumed centerline function which is of the Cauchy type in that the values and the derivatives of the function are known. Since the Cauchy boundary conditions can give rise to numerical instabilities, the governing gasdynamic equations for rotational steady flow were transformed into a form which puts the geometry into a rectangular shape, and which spaces the network of interior points more finely in regions of the greatest gradients of the dependent variables. For arbitrarily specified centerline data, the solution of the governing flow equations may not exist, and if it does it may not depend continuously on the data.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; June 197
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  • 46
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    Influence of contraction section shape and inlet flow direction on supersonic nozzle flow and performance. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Wall static pressure measurements and performance parameters are presented for axisymmetric supersonic nozzles with relatively steep convergent sections and comparatively small radius-of-curvature throats. The nozzle walls were essentially adiabatic. These results are compared with those obtained in other nozzles tested previously to appraise the influence of contraction shape on performance. Both the flow coefficient and the thrust were less than the corresponding values for one-dimensional, isentropic, plane flow for both the axial and radial inflow nozzles considered, but the specific impulse, the most important performance parameter, was found to be relatively unchanged. The thrust decrement for the axial inflow nozzles was established primarily by the shape of the contraction section, and could be estimated reasonably well from a conical sink flow consideration. The radial inflow nozzle has a potential advantage from a cooling point of view if used in a rocket engine.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; June 197
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  • 47
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    Cone transitional boundary-layer structure at Me = 14. (1972)
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    Publication Date: 2011-08-16
    Description: Experimental results suggest that the boundary-layer mean profiles in hypersonic flows may be highly transitional in the outer part of the boundary layer before the transition process is detected at the surface. Means of determining the initial location where the transition process begins in the outer part of the boundary layer are considered.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; May 1972
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  • 48
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    Thin-film light-intensity measurement strain-analysis technique. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The optical response to loading of a thin metallic film deposited on a low-modulus structural substrate is studied theoretically and experimentally. Two types of optical properties called total and central-image transmittance (or reflectance) are shown to be related to the mechanical state of the substrate. Empirical optical-mechanical relationships are proposed between these optical properties and the substrate strain field of a general plane-stress problem. A technique based on wrinkle and microfracture patterns is described for determining principal directions of strain. Experimental results for uniaxially loaded specimens show that it is possible to obtain a nearly linear relationship between transmittance and strain for certain materials combinations.
    Keywords: STRUCTURAL MECHANICS
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  • 49
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    A non-linear dynamic lumped-parameter model of a rectangular plate. (1972)
    In:  Other Sources
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    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
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  • 50
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    Solution of eigenvalue problems by Sturm sequence method. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A generalized eigenvalue algorithm is presented herein along with the complete listing of the associated computer program, which may be conveniently utilized for the efficient solution of certain broad classes of eigenvalue problems. Extensive applications of the procedure are envisaged in the analysis of many important engineering problems, such as stability and natural frequency analysis of practical discrete structural systems, idealized by the finite element technique. The procedure based on the Sturm sequence method is accurate and fast, possessing several significant advantages over other known methods of such analysis. Numerical results are also presented for two representative structural engineering problems.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal for Numerical Methods in Engineering; 4; May-June
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  • 51
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    Aerodynamic properties of spherical balloon wind sensors. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A first-order theory of the fluctuating lift and drag coefficients associated with the aerodynamically induced motions of rising and falling spherical wind sensors is developed. The equations of motion of a sensor are perturbed about an equilibrium state in which the buoyancy force balances the mean vertical drag force. It is shown that, to within first order in perturbation quantities, the aerodynamic lift force is confined to the horizontal, and the fluctuating drag force associated with fluctuations in the drag coefficient acts along the vertical. The perturbation equations are transformed with Fourier-Stieltjes integrals. The resulting equations lead to relationships between the power spectra of the aerodynamically induced velocity components and the spectra of the fluctuating lift and drag coefficients.
    Keywords: AERODYNAMICS
    Type: Journal of Applied Meteorology; 11; Apr. 197
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  • 52
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    Multiple-orifice liquid injection into hypersonic air streams. (1972)
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    Publication Date: 2011-08-16
    Description: Review of oblique water and fluorocarbon injection test results obtained in experimental studies of the effects of multiple-orifice liquid injection into hypersonic air streams. The results include the finding that maximum lateral penetration from such injections increases linearly with the square root of the jet-to-freestream dynamic-pressure ratio and is proportional to an equivalent orifice diameter.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Dec. 197
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  • 53
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    Effect of a circular hole on the buckling of cylindrical shells loaded by axial compression. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An experimental and analytical investigation of the effect of a circular hole on the buckling of thin cylindrical shells under axial compression was carried out. The experimental results were obtained from tests performed on seamless electroformed copper shells and Mylar shells with a lap joint seam. These results indicated that the character of the shell buckling was dependent on a parameter which is proportional to the hole radius divided by the square root of the product of the shell radius and thickness. For small values of this parameter, there was no apparent effect of the hole on the buckling load. For slightly larger values of the parameter, the shells still buckled into a general collapse configuration, but the buckling loads were sharply reduced as the parameter increased. For still larger values of the parameter, the buckling loads were further reduced, and the shells buckled into a stable local buckling configuration.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Nov. 197
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  • 54
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    Lee-side vortices on delta wings at hypersonic speeds. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A fluid-dynamic investigation was carried out to determine the cause of intense heating observed on the lee meridian of hypersonic delta wings and also to derive means for its suppression. Several experimental techniques were combined with analysis of extensive heat-transfer measurements at a freestream Mach number of six in a range of Reynolds number to acquire a general description of the lee-flow structure. With attached leading-edge flow on the delta wings, the dominant feature is a pair of embedded vortices on the lee meridian whose interaction with the boundary-layer is responsible for the observed local heating. On the basis of flow visualization results and heat-transfer correlations, a qualitative vortex flow model is proposed which differs essentially from the conventional inboard separation vortex model.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Nov. 197
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  • 55
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    Simplification of the wing-body interference problem. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 9; Oct. 197
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  • 56
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    Boron-aluminum structural component for Shuttle. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A boron-aluminum structural component, representative of Space Shuttle fuselage structure, has been fabricated and tested as part of a program to demonstrate boron-aluminum feasibility for Shuttle applications. The 4- by 5-foot component consists of eleven 24-ply Z section stringers and a +45 degree 8-ply skin. It was tested at room temperature and at 500 F under combined compressive and shear loadings. The components for this program were fabricated in order to encounter and solve scale-up problems, and to obtain test data representative of production hardware. The data from this program are expected to allow more accurate prediction of weights and costs of boron-aluminum structures for the Space Shuttle.
    Keywords: STRUCTURAL MECHANICS
    Type: SAMPE Quarterly; 3; July 197
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  • 57
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    Stored energy function of rubberlike materials derived from simple tensile data. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An explicit formulation is developed to obtain the stored energy function, based on the Valanis-Landel separable symmetric stored energy function. This formulation is applicable to any multiaxial stress state, from simple tensile data alone, for those cases in which the stored energy function is a separable function of the stretch ratios. By direct comparison, it is also shown that styrene butadiene rubber, at least over a specific range, follows this postulated separable form.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Applied Physics; 43; July 197
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  • 58
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    Oblique shock-sound interaction at a freestream Mach number of about 20 in helium. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Detailed experimental measurements of the characteristics and level of pre- and postshock disturbances obtained for typical disturbance modes and shock angles are presented to aid in the evaluation of transition studies conducted in 'noisy' hypersonic wind tunnels. The presented data suggest that the shock is probably generating total temperature fluctuations in a fashion directly related to shock strength. Since in high supersonic and hypersonic flows the total temperature fluctuations are mainly contained in velocity fluctuations, it may be concluded that the predominant disturbances generated are vorticity as long as the postshock flow is at a sufficiently high Mach number.-
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Dec. 197
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  • 59
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    Axisymmetric buckling of uniformly loaded spherical caps undergoing plastic deformation. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal; 10; Dec. 197
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  • 60
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    Fatigue and fracture basic research at the Langley Research Center. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: This paper gives some examples of projects underway. The projects are grouped according to the primary parameter being studied: loads, configuration, environment, or material. Significant topics include the effect of truncated loads, the effect of proof-tests, interference fasteners, accelerated and real-time tests for supersonic aircraft materials, crack-growth rates in built-up structures, and a model method by which material can be selected for a particular set of operating conditions.
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  • 61
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    Collocated interfacial stress intensity factors for finite bi-material plates. (1972)
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    Publication Date: 2011-08-16
    Description: This paper deals with elastic stress intensity factors associated with stress fields near partially debonded interfaces in finite, bi-material plates. Bi-material stress intensity factors K1 and K2 are not associated, respectively, with symmetric and skew-symmetric loading and are functions of an arbitrary length parameter. Any fracture condition involving bi-material stress intensity factors must be independent of the arbitrary length parameter and must be consistent with experiment. We define a new parameter called the interfacial stress intensity factor which satisfies the former condition. A truncated Williams power series stress function for stresses in a cracked bi-material plate, as modified by Sih and Rice, is used with a modified boundary collocation procedure to generate interfacial stress intensity factors for finite bi-material plates.
    Keywords: STRUCTURAL MECHANICS
    Type: Engineering Fracture Mechanics; 4; Dec. 197
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  • 62
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    Selective reinforcement of wing structure for flutter prevention. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The results of an analytical study are presented on the use of boron polyimide filamentary composite material for the purpose of increasing the flutter speed of a simple titanium full depth sandwich wing structure designed for strength. The results clearly demonstrate that selective reinforcement of wing surfaces, using judiciously placed filamentary composites, promises sizable mass savings in the design of advanced aircraft structures.
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft; 9; Nov. 197
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  • 63
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    Turbulent bursts and rings on a cone in helium at Me = 7.6. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of data obtained on turbulent burst geometry and growth characteristics for cone boundary-layer transition in a helium wind tunnel at a boundary-layer edge Mach number (Me) of 7.6. Detailed data concerning turbulent spot geometry and downstream propagation velocities were obtained using a spark schlieren system with sequential spark capability. In one particular test evidence of a symmetrical turbulent burst ring was obtained; all other bursts developed in a singular random manner. Profiles of the apparent outer edges of the bursts were obtained, and the velocities of the leading and trailing edges of the bursts relative to the local velocity were determined. The velocities of the leading and trailing edges were found to be fairly consistent for each observation, with the leading edge of the burst traveling at about local edge velocity, while the trailing edge moved supersonically relative to local speed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Oct. 197
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  • 64
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    Radiative and convective heating during Venus entry. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Determination of the stagnation region heating of probes entering the Venusian atmosphere. Both convective and radiative heat-transfer rates are predicted, and account is taken of the important effects of radiative transport in the vehicle shock layer. A nongray radiative transport model is utilized which parallels a four-band treatment previously developed for air (Page et al., 1969), but includes two additional bands to account for the important CO(4+) molecular band system. Some comparisons are made between results for Venus entry and results for earth entry obtained using a viscous earth entry program.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Oct. 197
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  • 65
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    Vibrations of circular elastic plates due to sonic boom. (1972)
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    Publication Date: 2011-08-16
    Description: The problem of transient axisymmetric vibrations of thin circular elastic plates due to sonic boom excitation is investigated. The equation of motion for a solid circular plate is solved by applying the modified finite Hankel transform and the Laplace transform, and the numerical results are obtained with the help of the digital computer. From the analysis of the data, obtained for the dynamic deflections of the plates for the boom duration, it is concluded that for a normal flight the boom duration has a significant effect on the vibrations of plates as compared to the overpressure of the boom.
    Keywords: STRUCTURAL MECHANICS
    Type: Acoustical Society of America; vol. 52
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  • 66
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    An Algorithm for Synthesizing Mass and Stiffness Matrices from Experimental Vibration Modes (1972)
    In:  CASI
    Details
    Publication Date: 2016-03-01
    Description: An algorithm is described for synthesizing the mass and stiffness matrices from experimentally derived modal data in a way that preserves the physical significance of the individual mass and stiffness elements. The mass and stiffness matrices are derived for a rollup solar array example, and are then used to define the modal response of a modified array.
    Keywords: STRUCTURAL MECHANICS
    Type: JPL Quart. Tech. Rev. ; Vol. 2; No. 3; p 12-21
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    Calculation of metric coefficients for streamline coordinates. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A procedure is given for deriving the equations describing the surface streamline metric in a general form and in a form suitable for incorporation into computer codes to calculate an inviscid flow about three-dimensional bodies. Sample results are included to show the application of the metric in conjunction with an axisymmetric analog to predict heat transfer to a typical space shuttle orbiter.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Nov. 197
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  • 68
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    Secondary jet interaction with emphasis on outflow and jet location. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Data were obtained concerning a model which utilized a two-dimensional sonic jet. It was found that outflow and jet location significantly influence the magnitude and behavior of the secondary jet interaction forces. Continued refinements in jet interaction analyses which do not account for outflow are of limited usefulness in the design of control systems for supersonic and hypersonic vehicles. The jet total back pressure ratio increases with either jet pressure ratio or freestream Mach number.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Nov. 197
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  • 69
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    Applications of NASTRAN substructuring (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of substructuring techniques are described for two example problems, a square plate and the static analysis of a frame-wall interaction problem in multistory structures. A DMAP routine for calculating the multipoint constraint forces is presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences e; p 485-496
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  • 70
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    Structural dynamic and thermal stress analysis of nuclear reactor vessel support system (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A nuclear reactor vessel is supported by a Z-ring and a box ring girder. The two proposed structural configurations to transmit the loads from the Z-ring and the box ring girder to the foundation are shown. The cantilever concrete ledge transmitting the load from the Z-ring and the box girder via the cavity wall to the foundation is shown, along with the loads being transmitted through one of the six steel columns. Both of these two supporting systems were analyzed by using rigid format 9 of NASTRAN for dynamic loads, and the thermal stresses were analyzed by AXISOL. The six column configuration was modeled by a combination of plate and bar elements, and the concrete cantilever ledge configuration was modeled by plate elements. Both configurations were found structurally satisfactory; however, nonstructural considerations favored the concrete cantilever ledge.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experience; p 465-475
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    Structural analysis for a 40-story building (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: NASTRAN was chosen as the principal analytical tool for structural analysis of the Illinois Center Plaza Hotel Building in Chicago, Illinois. The building is a 40-story, reinforced concrete structure utilizing a monolithic slab-column system. The displacements, member stresses, and foundation loads due to wind load, live load, and dead load were obtained through a series of NASTRAN runs. These analyses and the input technique are described.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 421-427
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    Applications of NASTRAN to nuclear problems (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The extent to which suitable solutions may be obtained for one physics problem and two engineering type problems is traced. NASTRAN appears to be a practical tool to solve one-group steady-state neutron diffusion equations. Transient diffusion analysis may be performed after new levels that allow time-dependent temperature calculations are developed. NASTRAN piecewise linear anlaysis may be applied to solve those plasticity problems for which a smooth stress-strain curve can be used to describe the nonlinear material behavior. The accuracy decreases when sharp transitions in the stress-strain relations are involved. Improved NASTRAN usefulness will be obtained when nonlinear material capabilities are extended to axisymmetric elements and to include provisions for time-dependent material properties and creep analysis. Rigid formats 3 and 5 proved to be very convenient for the buckling and normal-mode analysis of a nuclear fuel element.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences; p 429-441
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    A design study for the addition of higher order parametric discrete elements to NASTRAN (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The addition of discrete elements to NASTRAN poses significant interface problems with the level 15.1 assembly modules and geometry modules. Potential problems in designing new modules for higher-order parametric discrete elements are reviewed in both areas. An assembly procedure is suggested that separates grid point degrees of freedom on the basis of admissibility. New geometric input data are described that facilitate the definition of surfaces in parametric space.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 361-373
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    Some aspects of the NASTRAN program output (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The NASTRAN program output is discussed from a structural analysts point of view, and the simple modifications which were made to the program in order to improve it are also described. The convenience of the output for use in original design work is critically appraised and compared with the output from ASTRAL. It is shown that considerable hand calculation is necessary in order to extract useful load distribution data from the available NASTRAN output. For this reason, some effort was directed toward providing additional force output for the NASTRAN shear panel element.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 337-360
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    An isoparametric quadrilateral membrane element for NASTRAN (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The geometric and kinematic properties of the element are described, along with development of the matrices and vectors which characterize the element. The necessity for considering small deviations from element planeness is discussed, and the approach taken to account for these deviations is described. The improved accuracy over the existing quadrilateral membrane is indicated by a sample calculation for which an analytical solution is available from beam theory. For the same finite element idealization, the errors in maximum displacement and stress were significantly reduced.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences e; p 315-336
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    Adaptation of NASTRAN to an integrated system of structural design analysis (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Efforts to integrate NASTRAN into a complete structural analysis system for use by large airframe design projects are discussed. NASTRAN was implemented as a major finite element structural analysis program to determine the static and dynamic behavior of complete airframes, as well as structural components. This requires modifications and additions to NASTRAN, to communicate with an existing system, and to provide facilities needed to work within the integrated structural analysis. For this purpose, several special DMAP modules were developed and introduced into the CALAC version of the NASTRAN system.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 289-302
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  • 77
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    Comparison of NASTRAN and STARDYNE static analysis of a graphite fiber reinforced plastic truss structure (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A static and buckling analysis of the ATS-F&G spacecraft reflector support truss (RST) and bridge truss assembly using NASTRAN was conducted. The RST is fabricated from a new material, graphite fiber reinforced plastic. A comparison is made with the NASTRAN results and the results of a similar analysis conducted using the stardyne program. The results of an actual static load test are also compared.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences e; p 303-314
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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
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    Nonapplicability of linear finite element programs to the stress analysis of tires (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A static finite element stress analysis of an inflated radial car tire was carried out. The deformed shape of the sidewall presents outward bulging. The analysis of a homogeneous isotropic toroidal shell shows that the problem is common to all solids of this type. The study suggests that the geometric stiffness due to the inflation pressure has to be taken into account. Also, the resulting large displacements make it necessary for the geometry to be updated at each load step.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 263-276
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  • 80
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    Modeling techniques of thin walled beams with open cross sections (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A composite element is presented which includes the effects of warping and offset shear centers. It is shown to be mathematically consistent with thin walled open beam theory and can be incorporated into any structural analysis program by use of NASTRAN'S standard elements. A numerical example analyzing the vibration of a channel beam is presented, and, by using the composite element, the numerical results agreed well with theoretical data.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 179-195
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    Complex eigenvalue analysis of rotating structures (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A FORTRAN subroutine to NASTRAN which constructs coriolis and centripetal acceleration matrices, and a centrifugal load vector due to spin about a selected point or about the mass center of the structure is discussed. The rigid translational degrees of freedom can be removed by using a transformation matrix T and its explicitly given inverse. These matrices are generated in the subroutine and their explicit expressions are given.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences; p 197-234
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    Level 12 NASTRAN experiences at General Dynamics, Convair Aerospace Division, Fort Worth Operations (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The level 12 NASTRAN was used to support the NASA/LaRC advanced transport technology study, a predesign, short response time effort. Aeroelastic analyses were performed. NASTRAN calculated the vibration modes for the supported airfoil components and the entire unsupported vehicle. Other procedures were then used for the aeroelastic analysis, with procedure interfacing accomplished through use of the NASTRAN-produced restart tape. Stiffness matrices were used in static aeroelastic analyses; natural vibration modes were used for flutter and flight control system definition. Various level 12 NASTRAN characteristics were discovered and are discussed; e.g., the ability to solve singular matrices in rigid format 1, run times using multipoint constraints, restart tape problems, and the inaccurate stresses from the quad membrane when used with anisotropic materials.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 235-261
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  • 83
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    Transient analysis of an IVHM grapple impact test (1972)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: A lumped mass model was used to represent the impact condition between a fuel duct and an IVHM in-vessel fuel handling machine. The nonlinear effects of a Bellville spring and the free fall impact of the fuel duct on the IVHM were included. The purpose of the tests was to determine the loads on the fuel duct due to the impact. A comparison between experimental and theoretical results is presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 161-178
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    A NASTRAN correlation study for vibrations of a cross-stiffened ship's deck (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: To evaluate the effectiveness of NASTRAN for predicting the vibration modes of panels with bending-membrane coupling, a cross-stiffened ship deck was analyzed. In correlation with experimental data, one NASTRAN finite element representation gave results slightly more accurate than a previous analytical solution. Computational time was excessively long, due to the Guyan method of reducing the eigenvalue problem. It is recommended that a more efficient method of matrix reduction be implemented for the lumped mass formulation.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 145-159
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    Delta launch vehicle isogrid structure NASTRAN analysis (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Structural analysis applications of NASTRAN to the isogrid structure of the Delta launch vehicle are discussed. Isogrid is a method employed to stiffen the booster cylindrical shell surface by integrally machining ribs and skin from one piece of metal. The ribs are arranged in a repetitive equilateral triangular pattern; this results in a structural surface whose stiffness is orthogonally isotopic. For that structure, both static and general instability buckling analyses are described and the theoretical results are compared to test data. One of the parameters included in the analysis is the effect of pressure loadings on the buckling allowable load. In addition, a description of a supplementary computer program is presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences; p 121-143
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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
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  • 87
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    Analysis and design of on-grade reinforced concrete track support structures (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: For the improvement of rail service, the Department of Transportation, Federal Rail Administration, is sponsoring a test track on the Atchison, Topeka, and Santa Fe Railway. The test track will contain nine separate rail support structures, including one conventional section for control and three reinforced concrete structures on grade, one slab and two beam sections. The analysis and design of these latter structures was accomplished by means of the finite element method, NASTRAN, and is presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 99-110
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  • 88
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    Stress and buckling analysis of a double-bubble tank structure (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An analytical study of a two-lobed circular arc pressure vessel (double-bubble tank) with a local perturbation from the cylindrical shape was made. It can be concluded that NASTRAN provides a good linear buckling analysis capability for structures that cannot be handled by other analysis techniques. However, solutions are relatively expensive from a computational standpoint. Two worthwhile additions to the NASTRAN program would be the inclusion of a new beam element that adequately represents the shear transfer when modeling stiffeners on a shell and the capability, in a rigid format, to keep certain prescribed loads constant during the eigenvalue extraction process.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences; p 53-71
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    NASTRAN buckling analysis of a thin walled cylinder (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The computer run time required for a buckling analysis using NASTRAN is considerably greater than for a linear static analysis of the same structure. It is very important to obtain an optimal model size for the structure being analyzed, such that the model is neither so large as to increase running time unnecessarily, nor so small as to hinder accuracy. The problem of critical load accuracy versus model complexity is considered for a thin walled cylinder, using both Level 12 and Level 15 NASTRAN releases.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences; p 39-51
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  • 90
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    Buckling analysis of a missile interstage (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The NASTRAN program was used to find the buckling location and the degradation factor due to a specified temperature field for an interstage of a typical three stage missile. The model was made up of 6332 independent degrees of freedom. This large size required the use of an IBM 370/195 for evaluation of the eigenvalues. The effect of elevated temperature was to lower the critical buckling load by 3%.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center NASTRAN: Users' Experiences; p 29-38
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    Some applications of NASTRAN to the buckling of thin cylindrical shells with cutouts (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The buckling of isotropic and waffle-stiffened circular cylinders with and without cutouts was studied using NASTRAN's Rigid Format 5 for the case of axial compressive loading. The results obtained for the cylinders without cutouts are compared with available reference solutions. The results for the isotropic cylinders containing a single circular cutout with selected radii are compared with available experimental data. For the waffle-stiffened cyclinder, the effect of two diametrically opposed rectangular cutouts was studied. A DMAP alter sequence was used to permit the necessary application of different prebuckling and buckling boundary conditions. Advantage was taken of available symmetry planes to formulate equivalent NASTRAN model segments which reduced the associated computational cost of performing the analyses. Limitations of the applicability of NASTRAN for the solution of problems with nonlinear characteristics are discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences; p 73-97
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  • 92
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    NASTRAN: A progress report (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Significant NASTRAN-related events since September, 1971 are reviewed. The present operation of the NASTRAN systems management office is described, as well as new capabilities and improvements incorporated in Level 15 of NASTRAN, and priorities for future levels of NASTRAN.
    Keywords: STRUCTURAL MECHANICS
    Type: NASTRAN: Users' Experiences; p 1-11
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  • 93
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    Structural testing of concorde aircraft: Further report on United Kingdom tests (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A summary of tests conducted on the Concorde aircraft nacelle structure is presented. The tests were conducted as a part of the structural development and certification program. The nacelle structural specimens are described. The problems associated with the intake testing and engine-bay and nozzle testing are discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluations; p 649-665
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    Fatigue tests on big structure assemblies of concorde aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Fatigue tests on structural assemblies of the Concorde supersonic transport aircraft are reported. Two main sections of the aircraft were subjected to pressure, mechanical load, and thermal static tests. The types of fatigue tests conducted and the results obtained are discussed. It was concluded that on a supersonic aircraft whose structural weight is a significant part of the weight analysis, many fatigue and static strength development tests should be made and fatigue and thermal tests of the structures are absolutely necessary.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation; p 631-648
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    Detection of structural deterioration and associated airline maintenance problems (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Airline operations involving the detection of structural deterioration and associated maintenance problems are discussed. The standard approach to the maintenance and inspection of aircraft components and systems is described. The frequency of inspections and the application of preventive maintenance practices are examined. The types of failure which airline transport aircraft encounter and the steps taken to prevent catastrophic failure are reported.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation; p 599-609
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    Statistical load data processing (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A recorder system has been installed on two operational fighter aircrafts. Signal values from a c.g.-acceleration transducer and a strain-gage installation at the wing root were sampled and recorded in digital format on the recorder system. To analyse such load-time histories for fatigue evaluation purposes, a number of counting methods are available in which level crossings, peaks, or ranges are counted. Ten different existing counting principles are defined. The load-time histories are analysed to evaluate these counting methods. For some of the described counting methods, the counting results might be affected by arbitrarily chosen parameters such as the magnitude of load ranges that will be neglected and other secondary counting restrictions. Such influences might invalidate the final counting results entirely. The evaluation shows that for the type of load-time histories associated with most counting methods, a sensible value of the parameters involved can be found.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation; p 565-598
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    The influence of modifications of a fatigue loading history program on fatigue lifetime (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Rectangular specimens of 7075 and 2014 aluminum alloys with two holes (stress concentration factor of 3.24) have been tested under axial fatigue loading on a six-rod test bed with modifications of the loading program, the surface particulars, and the frequency. The length of the precrack stage was investigated by use of a new crack detector. In most cases the two alloys behaved similarly, with similar life to crack start under the same loading. Some overloads lengthened the life. Truncation by omission of the lowest peak loads should be limited to about 20 percent of the ultimate load. Simplifying counting methods gave misleading results. Very thin surface layers of anodizing, protection by vinyl, dry nitrogen atmosphere, as well as stepwise reaming or grinding the surface of the holes, lengthened the life; thick anodized layers shortened the life. Compressing the hole surface by rolling had no influence. Frequencies at about 210 to 240 cpm produced shorter lives than those at 40 cpm. At 5.4 cpm the life was considerably longer. A model to better understand the precrack-stage fatigue mechanism is discussed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation; p 485-539
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    Fracture control procedures for aircraft structural integrity (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of applied fracture mechanics in the design, analysis, and qualification of aircraft structural systems are reviewed. Recent service experiences are cited. Current trends in high-strength materials application are reviewed with particular emphasis on the manner in which fracture toughness and structural efficiency may affect the material selection process. General fracture control procedures are reviewed in depth with specific reference to the impact of inspectability, structural arrangement, and material on proposed analysis requirements for safe crack growth. The relative impact on allowable design stress is indicated by example. Design criteria, material, and analysis requirements for implementation of fracture control procedures are reviewed together with limitations in current available data techniques. A summary of items which require further study and attention is presented.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation; p 437-483
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  • 99
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    A parametric approach to irregular fatigue prediction (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A parametric approach to irregular fatigue protection is presented. The method proposed consists of two parts: empirical determination of certain characteristics of a material by means of a relatively small number of well-defined standard tests, and arithmetical application of the results obtained to arbitrary loading histories. The following groups of parameters are thus taken into account: (1) the variations of the mean stress, (2) the interaction of these variations and the superposed oscillating stresses, (3) the spectrum of the oscillating-stress amplitudes, and (4) the sequence of the oscillating-stress amplitudes. It is pointed out that only experimental verification can throw sufficient light upon possibilities and limitations of this (or any other) prediction method.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation te; p 429-436
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    Practical aspects of designing for and evaluating structural integrity (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of procedures for designing and evaluating structural integrity of various construction techniques is discussed. The fatigue performance improvement of the following conditions is described: (1) conical fasteners, (2) hole preparation, (3) interference fit, and (4) interference protection. The application of fatigue tests to determine fail-safe conditions is analyzed.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation te; p 405-424
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