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  • Articles
  • Other Sources  (221)
  • NASA Technical Reports  (221)
  • Bibliography on Seismology
  • AERODYNAMICS  (125)
  • MECHANICAL ENGINEERING  (55)
  • COMPOSITE MATERIALS  (41)
  • 1980-1984  (221)
  • 1965-1969
  • 1983  (221)
Collection
  • Articles
  • Other Sources  (221)
Source
  • NASA Technical Reports  (221)
  • Bibliography on Seismology
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  • 1980-1984  (221)
  • 1965-1969
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  • 1
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    Advanced technology exhaust nozzle development (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The requirement for greater tactical aircraft operational capabilities has led to increasing research emphasis on the refinement of engine/airframe integration methods and exhaust nozzle flexibility. A major prospective advancement in the development of these capabilities takes the form of multifunctional exhaust nozzle systems with thrust reversal and thrust vectoring features, whose operation will be shared by both airframe and powerplant control systems. Attention is presently given to the two-dimensional convergent-divergent and single expansion ramp nozzle designs, with emphasis on the variable geometry mechanical systems by which they assume cruising flight, vectoring, and thrust reversal operations. The nozzles have been wind tunnel model-tested for the cases of the F-18 fighter and a supersonic cruise configuration concept.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1286
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Full-scale testing, production and cost analysis data for the advanced composite stabilizer for Boeing 737 aircraft. Volume 1: Technical summary (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The full scale ground test, ground vibration test, and flight tests conducted to demonstrate a composite structure stabilizer for the Boeing 737 aircraft and obtain FAA certification are described. Detail tools, assembly tools, and overall production are discussed. Cost analyses aspects covered include production costs, composite material usage factors, and cost comparisons.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-3649 , NAS 1.26:3649 , D6-46038-1-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Design, ancillary testing, analysis and fabrication data for the advanced composite stabilizer for Boeing 737 aircraft. Volume 1: Technical summary (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The horizontal stabilizer of the 737 transport was redesigned. Five shipsets were fabricated using composite materials. Weight reduction greater than the 20% goal was achieved. Parts and assemblies were readily produced on production-type tooling. Quality assurance methods were demonstrated. Repair methods were developed and demonstrated. Strength and stiffness analytical methods were substantiated by comparison with test results. Cost data was accumulated in a semiproduction environment. FAA certification was obtained.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-3648 , NAS 1.26:3648 , D6-46037-1-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Stability of shock waves attached to wedges and cones (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 06, p. 799, Accession no. A82-17876
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 21; 1611-161
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Thermal and mechanical properties of advanced, high temperature ceramic-composite insulation (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: It is found that the mechanical properties of fibrous refractory composite insulation (FRCI) can be improved if a higher calcination temperature is used before final processing. The results also reveal that a higher density FRCI containing 60 wt pct aluminoborosilicate fibers will exhibit minimal surface recession at 1480 C in a convective-heating environment. Another finding is that the material performance in the convective-heating environment is limited by the coating and the temperature capability of its emittance agent. A table is included giving the coating compositions used with the composite insulation and tested in the convectively heated environment at a surface temperature of 1480 C.
    Keywords: COMPOSITE MATERIALS
    Type: Ceramic Engineering and Science Proceedings (ISSN 0196-6219); 4; 551-563
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    NASA TECHNICAL REPORTS
  • 6
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    Unsteady transonic small disturbance approximation with strong shock waves (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 06, p. 797, Accession no. A82-17812
    Keywords: AERODYNAMICS
    Type: (ISSN 0001-1452)
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Interlaminar shear properties of graphite fiber, high-performance resin composites (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Short beam testing was used to determine the shear properties of laminates consisting of T-300 and Celion 3000 and 6000 graphite fibers, in epoxy, hot melt and solvent bismaleimide, polyimide and polystyrylpyridine (PSP). Epoxy, composites showed the highest interlaminar shear strength, with values for all other resins being substantially lower. The dependence of interlaminar shear properties on the fiber-resin interfacial bond and on resin wetting characteristics and mechanical properties is investigated, and it is determined that the lower shear strength of the tested composites, by comparison with epoxy resin matrix composites, is due to their correspondingly lower interfacial bond strengths. An investigation of the effect of the wettability of carbon fiber tow on shear strength shows wetting variations among resins that are too small to account for the large shear strength property differences observed.
    Keywords: COMPOSITE MATERIALS
    Type: Polymer Composites (ISSN 0272-8397); 4; April 19
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    NASA TECHNICAL REPORTS
  • 8
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    Double arch mirror study (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The development of a method of mounting light weight glass mirrors for astronomical telescopes compatible with the goals of the Shuttle Infrared Telescope Facility (SIRTF) was investigated. A 20 in. diameter double arch lightweight mirror previously fabricated was modified to use a new mount configuration. This mount concept was developed and fabricated. The mounting concept of the double mounting mirror is outlined. The modifications made to the mirror, fabrication of the mirror mount, and room temperature testing of the mirror and mount and the extension of the mirror and mount concept to a full size (40 in. diameter) primary mirror for SIRTF are discussed.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-166589 , NAS 1.26:166589
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Double arch mirror study. Part 1: Preliminary engineering report (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the proposed design, the NASA AMES 20-in double arch mirror is supported by three clamp and flexure assemblies. The mirror clamp consists of a T-shaped Invar-36 member that goes into a similarly shaped socket in the back of the mirror. The mirror socket is made oversize and contacts the clamp only along the conical surface. The clamp is preloaded by a spring washer and pulls the mirror into contact with the flexure. The clamp is then inserted into the mirror socket through a cutout, is rotated 90 deg, and is then pinned in place. Loading conditions considered in socket design are discussed as well as stress in the socket and clamp. Flexure geometry and stress are examined as well as the effects of flexure error and of mirror cell error.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-166589-PT-1 , NAS 1.26:166589-PT-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Convair 990 transonic flow-field simulation about the forward fuselage (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A three-dimensional, viscous flow code was used to calculate the transonic flow about the forebody of the Convair CV-990 (Galileo II) research aircraft stationed at NASA Ames Research Center. The computations were used to determine the location for a differential pressure system. In addition, attitude sensor placements were verified. These instruments comprise a meteorological measurement system, which will be used for global determination of three-dimensional wind data. The code solves the thin layer form of the Reynolds-averaged Navier-Stokes equations using an implicit numerical procedure. The governing equations are written in a generalized, nonorthogonal coordinate system, and are cast in a strong conservation law form. Laminar boundary layer results are presented for free stream Mach number of 0.8 and angles of attack of zero and 2 deg. Use of this computational tool reduced the development time for the location of the sensors and aided in the optimal placement on the aircraft of these devices.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1785
    Format: text
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    NASA TECHNICAL REPORTS
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