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  • COMMUNICATIONS  (61)
  • STRUCTURAL MECHANICS  (57)
  • ASTROPHYSICS
  • AUXILIARY SYSTEMS
  • 1985-1989
  • 1970-1974  (159)
  • 1960-1964
  • 1972  (159)
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Keywords
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  • 1985-1989
  • 1970-1974  (159)
  • 1960-1964
Year
  • 1
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    Residual strength and crack propagation tests on C-130 airplane center wings with service-imposed fatigue damage (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Fourteen C-130 airplane center wings, each containing service-imposed fatigue damage resulting from 4000 to 13,000 accumulated flight hours, were tested to determine their fatigue crack propagation and static residual strength characteristics. Eight wings were subjected to a two-step constant amplitude fatigue test prior to static testing. Cracks up to 30 inches long were generated in these tests. Residual static strengths of these wings ranged from 56 to 87 percent of limit load. The remaining six wings containing cracks up to 4 inches long were statically tested as received from field service. Residual static strengths of these wings ranged from 98 to 117 percent of limit load. Damage-tolerant structural design features such as fastener holes, stringers, doublers around door cutouts, and spanwise panel splices proved to be effective in retarding crack propagation.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-2075 , ER-11178
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Preliminary design of an auxiliary power unit for the space shuttle. Volume 4: Selected system supporting studies (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Selected system supporting analyses in conjunction with the preliminary design of an auxiliary power unit (APU) for the space shuttle are presented. Both steady state and transient auxiliary power unit performance, based on digital computer programs, were examined. The selected APU provides up to 400 horsepower out of the gearbox, weighs 227 pounds, and requires 2 pounds per shaft horsepower hour of propellants.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-1996 , REPT-71-7300-3.2-VOL-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Preliminary design of an auxiliary power unit for the space shuttle. Volume 5: Selected system cycle performance data (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Detailed cycle steady-state performance data are presented for the final auxiliary power unit (APU) system configuration. The selection configuration is a hydrogen-oxygen APU incorporating a recuperator to utilize the exhaust energy and using the cycle hydrogen flow as a means of cooling the component heat loads. The data are given in the form of computer printouts and provide the following: (1) verification of the adequacy of the design to meet the problem statement for steady-state performance; (2) overall system performance data for the vehicle system analyst to determine propellant consumption and hydraulic fluid temperature as a function for varying mission profiles, propellant inlet conditions, etc.; and (3) detailed component performance and cycle state point data to show what is happening in the cycle as a function of the external forcing functions.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-1997 , REPT-71-7300-3.3
    Format: application/pdf
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  • 4
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    Preliminary design of an auxiliary power unit for the space shuttle. Volume 2: Component and system configuration screening analysis (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The auxiliary power unit (APU) for the space shuttle is required to provide hydraulic and electrical power on board the booster and orbiter vehicles. Five systems and their associated components, which utilize hot gas turbines to supply horsepower at gearbox output pads, were studied. Hydrogen-oxygen and storable propellants were considered for the hot gas supply. All APU's were required to be self contained with respect to dissipating internally generated heat. These five systems were evaluated relative to a consistent criteria. The system supplied with high pressure gaseous hydrogen and oxygen was recommended as the best approach. It included a two-stage pressure-compounded partial-admission turbine, a propellant conditioning system with recuperation, a control system, and a gearbox. The gearbox output used was 240 HP. At the close of the study a 400 HP level was considered more appropriate for meeting the prime shuttle vehicle needs, and an in-depth analysis of the system at the 400 HP output level was recommended.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-1994 , REPT-71-7300-2-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Preliminary design of an auxiliary power unit for the space shuttle. Volume 1: Summary (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Numerous candidate APU concepts are considered, each meeting the space shuttle APU problem statement. Evaluation of these concepts indicates that the optimum concept is a hydrogen-oxygen APU incorporating a recuperator to utilize the exhaust energy and using the cycle hydrogen flow as a means of cooling the component heat loads. A preliminary design of the selected APU concept is presented, placing primary emphasis on the cycle thermal management and the controls. Results for both steady state and transient APU performance are also included, based on digital computer programs developed during the study. The selected APU provides up to 400 hp out of the gearbox, has a fixed weight of about 277 lb, and requires about 2 lb/shp-hr of propellants.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-1993 , REPT-71-7300-1-VOL-1
    Format: application/pdf
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  • 6
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    Preliminary design of an auxiliary power unit for the space shuttle. Volume 3: Details of system analysis, engineering, and design for selected system (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Numerous candidate APU concepts, each meeting the space shuttle APU problem statement are considered. Evaluation of these concepts indicates that the optimum concept is a hydrogen-oxygen APU incorporating a recuperator to utilize the exhaust energy and using the cycle hydrogen flow as a means of cooling the component heat loads.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-1995 , REPT-71-7300-3.1-VOL-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Optimum mass-strength analysis for orthotropic ring-stiffened cylinders under axial compression (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis was developed to calculate the minimum mass-strength curve for an orthotropic cylinder subjected to axial compressive loading. The analysis, which includes the effects of ring and stringer eccentricities, is in a general form so that various cylinder wall and stiffener geometries can be considered. Several different ring-stiffened orthotropic configurations were studied. The minimum mass-strength curves and the dimensions associated with these curves are presented for (in order of decreasing efficiency) a tubular double bead, a nonsymmetric double bead, a Z-stiffened skin, and a trapezoidal corrugation. A comparison of efficiencies of the configurations shows a tubular element cylinder to be more efficient than a 3-percent core-density honeycomb-sandwich cylinder. It was found that for an optimized Z-stiffened skin, the location of the Z-stiffeners (internal or external) made a negligible difference in efficiency.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-6772 , L-7060
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    ATS-F COMSAT millimeter wave propagation experiment. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Description of the transmitting and receiving system configurations to be used in an ATS-F propagation experiment designed to gather data on the attenuation of satellite uplink signals (at approximately 13.2 and 17.8 GHz) due to atmospheric hydrometeors (mostly rain). The data will be used for statistical determination of system power margins required for operational communications systems at frequencies above 10 GHz. A secondary analysis will study site diversity as a means of reducing the required system margins. A spacecraft transponder receives signals from 15 dual-frequency ground transmitter stations and retransmits these signals to a central ground receiving terminal at a frequency of 4 GHz.
    Keywords: COMMUNICATIONS
    Type: NTC ''72; National Telecommunications Conference; Dec 04, 1972 - Dec 06, 1972; Houston, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Analysis of the transient response of shell structures by numerical methods. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper examines some basic considerations underlying dynamic shell response analysis and the impact of these considerations upon the practical aspects of solution by numerical methods. Emphasis is placed on the solution of linear problems. The present states of development of the finite difference and finite element methods are reviewed, and techniques for the treatment of temporal variation are discussed. An examination is made of the frequency parameters characteristic of thin shell theory, applied excitations, and spatial mesh geometries, and the significance of these parameters with respect to computational convergence is illustrated.
    Keywords: STRUCTURAL MECHANICS
    Type: Dynamic response of structures; Symposium; Jun 28, 1971 - Jun 29, 1971; Stanford, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Automated procedures for sizing aerospace vehicle structures /SAVES/ (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results from a continuing effort to develop automated methods for structural design are described. A system of computer programs presently under development called SAVES is intended to automate the preliminary structural design of a complete aerospace vehicle. Each step in the automated design process of the SAVES system of programs is discussed, with emphasis placed on use of automated routines for generation of finite-element models. The versatility of these routines is demonstrated by structural models generated for a space shuttle orbiter, an advanced technology transport,n hydrogen fueled Mach 3 transport. Illustrative numerical results are presented for the Mach 3 transport wing.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 72-332 , Structures, Structural Dynamics, and Materials Conference; Apr 10, 1972 - Apr 12, 1972; San Antonio, TX
    Format: text
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