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  • Other Sources  (44)
  • Launch Vehicles and Launch Operations  (22)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (13)
  • STRUCTURAL MECHANICS  (9)
  • 2005-2009  (22)
  • 1975-1979  (22)
  • 1
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    Fatigue failure load indicator (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An indicator for recording the load at which a fatigue specimen breaks during the last cycle of a fatigue test is described. A load cell is attached to the specimen which is alternately subjected to tension and compression loads. The output of the load cell which is proportional to the load on the specimen is applied to the input of a peak detector. Each time the specimen is subjected to a compression load, means are provided for applying a positive voltage to the rest of the peak detector to reset it. During the last cycle of the tension load the peak detector measures the maximum load on the specimen. Means are provided for disconnecting the load cell from the peak detector when there is a failure in the specimen.
    Keywords: STRUCTURAL MECHANICS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Constellation Launch Vehicles Overview (2009)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This slide presentation reviews the current status of the launch vehicles associated with the Constellation Program. These are the Ares I and the Ares V. An overview of the Ares launch vehicles is included. The presentation stresses that the major criteria for the Ares I launcher is the safety of the crew, and the presentation reviews the various features that are designed to assure that aim. The Ares I vehicle is being built on a foundation of proven technologies, and the Ares V will give NASA unprecedented performance and payload volume that can enable a range of future missions. The CDs contain videos of scenes from various activities surrounding the design, construction and testing of the vehicles.
    Keywords: Launch Vehicles and Launch Operations
    Type: Human Space Flight Review; Jul 29, 2009; Huntsville, AL; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced structures technology applied to a supersonic cruise arrow-wing configuration (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of advanced technology to a promising aerodynamic configuration was explored to investigate the improved payload range characteristics over the configuration postulated during the National SST Program. The results of an analytical study performed to determine the best structural approach for design of a Mach number 2.7 arrow-wing supersonic cruise aircraft are highlighted. The data conducted under the auspices of the Structures Directorate of the National Aeronautics and Space Administration, Langley Research Center, established firm technical bases from which further trend studies were conducted to quantitatively assess the benefits and feasibility of using advanced structures technology to arrive at a viable advanced supersonic cruise aircraft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Res. Center Proc. of the SCAR Conf., Pt. 2,; 34 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Effect of end-ring stiffness on buckling of pressure-loaded stiffened conical shells (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Buckling studies were conducted on truncated 120 deg conical shells having large end rings and many interior reinforcing rings that are typical of aeroshells used as spacecraft decelerators. Changes in base-end-ring stiffness were accomplished by simply machining away a portion of the base ring between successive buckling tests. Initial imperfection measurements from the test cones were included in the analytical model.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TP-1079 , L-11915
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Buckling tests of three 4.6 meter diameter aluminum honeycomb sandwich conical shells loaded under external pressure (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three aluminum honeycomb sandwich conical shells with a 120 apex angle and a 4.6-m (15.0-ft) base diameter were loaded to failure by a uniform external pressure. The cones differed from one another only in the thickness of their respective face sheets. Test specimen details, test procedure, and test results are discussed. Both buckling and prebuckling data are compared with appropriate theoretical predictions, and good agreement was obtained between test and theory. Extensive imperfection measurements were made and reported on the three cones in the as fabricated condition.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TN-D-7935 , L-9936
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Arrow-wing supersonic cruise aircraft structural design concepts evaluation. Volume 1: Sections 1 through 6 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The structural approach best suited for the design of a Mach 2.7 arrow-wing supersonic cruise aircraft was investigated. Results, procedures, and principal justification of results are presented. Detailed substantiation data are given. In general, each major analysis is presented sequentially in separate sections to provide continuity in the flow of the design concepts analysis effort. In addition to the design concepts evaluation and the detailed engineering design analyses, supporting tasks encompassing: (1) the controls system development; (2) the propulsion-airframe integration study; and (3) the advanced technology assessment are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132575-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Arrow-wing supersonic cruise aircraft structural design concepts evaluation. Volume 3: Sections 12 through 14 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design of an economically viable supersonic cruise aircraft requires the lowest attainable structural-mass fraction commensurate with the selected near-term structural material technology. To achieve this goal of minimum structural-mass fraction, various combinations of promising wing and fuselage primary structure were analyzed for the load-temperature environment applicable to the arrow wing configuration. This analysis was conducted in accordance with the design criteria specified and included extensive use of computer-aided analytical methods to screen the candidate concepts and select the most promising concepts for the in-depth structural analysis.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132575-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Arrow-wing supersonic cruise aircraft structural design concepts evaluation. Volume 4: Sections 15 through 21 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analyses performed to provide structural mass estimates for the arrow wing supersonic cruise aircraft are presented. To realize the full potential for structural mass reduction, a spectrum of approaches for the wing and fuselage primary structure design were investigated. The objective was: (1) to assess the relative merits of various structural arrangements, concepts, and materials; (2) to select the structural approach best suited for the Mach 2.7 environment; and (3) to provide construction details and structural mass estimates based on in-depth structural design studies. Production costs, propulsion-airframe integration, and advanced technology assessment are included.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132575-4
    Format: application/pdf
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  • 9
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    Arrow-wing supersonic cruise aircraft structural design concepts evaluation. Volume 2: Sections 7 through 11 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The materials and advanced producibility methods that offer potential structural mass savings in the design of the primary structure for a supersonic cruise aircraft are identified and reported. A summary of the materials and fabrication techniques selected for this analytical effort is presented. Both metallic and composite material systems were selected for application to a near-term start-of-design technology aircraft. Selective reinforcement of the basic metallic structure was considered as the appropriate level of composite application for the near-term design.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132575-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Identifying and analyzing methods for reducing the energy consumption of helicopters (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of a study to identify those helicopter technology areas which would result in the largest energy (or fuel) savings when applied to large tandem (100 passenger) civil helicopters in the 1985 time frame. Baseline aircraft using 1975 technology in the areas of powerplant, rotor efficiency, parasite drag and structure were sized to a very short haul mission of 100 N.M. and a short haul mission of 200 N.M. A systematic parametric analysis was then conducted to assess the impact of technology improvements. Projections of the technology levels that could be obtained in the 1985 time frame were made and the resources estimated to achieve them. Based on these data, the highest payoff (lowest energy) helicopter technologies are identified.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144953 , D210-11007-1
    Format: application/pdf
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