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  • INSTRUMENTATION AND PHOTOGRAPHY  (91)
  • AERODYNAMICS  (55)
  • 1980-1984
  • 1970-1974  (146)
  • 1950-1954
  • 1973  (146)
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  • 1980-1984
  • 1970-1974  (146)
  • 1950-1954
Year
  • 1
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 4: IPAD system design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The computing system design of IPAD is described and the requirements which form the basis for the system design are discussed. The system is presented in terms of a functional design description and technical design specifications. The functional design specifications give the detailed description of the system design using top-down structured programming methodology. Human behavioral characteristics, which specify the system design at the user interface, security considerations, and standards for system design, implementation, and maintenance are also part of the technical design specifications. Detailed specifications of the two most common computing system types in use by the major aerospace companies which could support the IPAD system design are presented. The report of a study to investigate migration of IPAD software between the two candidate 3rd generation host computing systems and from these systems to a 4th generation system is included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132394 , D6-60181-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 1A: Summary (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: IPAD was defined as a total system oriented to the product design process. This total system was designed to recognize the product design process, individuals and their design process tasks, and the computer-based IPAD System to aid product design. Principal elements of the IPAD System include the host computer and its interactive system software, new executive and data management software, and an open-ended IPAD library of technical programs to match the intended product design process. The basic goal of the IPAD total system is to increase the productivity of the product design organization. Increases in individual productivity were feasible through automation and computer support of routine information handling. Such proven automation can directly decrease cost and flowtime in the product design process.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132390 , D6-60181-1A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    PAET, an entry probe experiment in the earth's atmosphere. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Description of the instrumentation of a probe designed for atmospheric studies on other planets and designated PAET. The probe was launched on June 20, 1971, near Bermuda in a trial experiment for measurements of the structure and composition of the terrestrial atmosphere. The instrumentation included accelerometers, pressure and temperature sensors, a mass spectrometer, and a radiometer. The measurements, carried out during the descent of the probe from an altitude of 90 km into the sea, were a success.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Icarus; 18; Apr. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    The color bar phase meter: A simple and economical method for calibrating crystal oscillators (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Comparison of crystal oscillators to the rubidium stabilized color burst is made easy and inexpensive by use of the color bar phase meter. Required equipment consists of an unmodified color TV receiver, a color bar synthesizer and a stop watch (a wrist watch or clock with sweep second hand may be used with reduced precision). Measurement precision of 1 x 10 to the minus 10th power can be realized in measurement times of less than two minutes. If the color bar synthesizer were commercially available, user cost should be less than $200.00, exclusive of the TV receiver. Parts cost for the color bar synthesizer which translates the crystal oscillator frequency to 3.579MHz and modulates the received RF signal before it is fed to the receiver antenna terminals is about $25.00. A more sophisticated automated version, with precision of 1 x 10 to the minus 11th power would cost about twice as much.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Goddard Space Flight Center Proc. of the 5th Ann. NASA and DOD Precise Time and Time Interval Planning Meeting; p 503-504
    Format: application/pdf
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  • 5
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 6: IPAD system development and operation (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The strategy of the IPAD implementation plan presented, proposes a three phase development of the IPAD system and technical modules, and the transfer of this capability from the development environment to the aerospace vehicle design environment. The system and technical module capabilities for each phase of development are described. The system and technical module programming languages are recommended as well as the initial host computer system hardware and operating system. The cost of developing the IPAD technology is estimated. A schedule displaying the flowtime required for each development task is given. A PERT chart gives the developmental relationships of each of the tasks and an estimate of the operational cost of the IPAD system is offered.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132396 , D6-60181-6
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 1B: Concise review (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Reports on the design process, support of the design process, IPAD System design catalog of IPAD technical program elements, IPAD System development and operation, and IPAD benefits and impact are concisely reviewed. The approach used to define the design is described. Major activities performed during the product development cycle are identified. The computer system requirements necessary to support the design process are given as computational requirements of the host system, technical program elements and system features. The IPAD computer system design is presented as concepts, a functional description and an organizational diagram of its major components. The cost and schedules and a three phase plan for IPAD implementation are presented. The benefits and impact of IPAD technology are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132391 , D6-60181-1B
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Performance of transonic fan stage with weight flow per unit annulus area of 178 kilograms per second per square meter (6.5(lb/sec)/(sq ft)) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The overall and blade-element performances are presented over the stable flow operating range from 50 to 100 percent of design speed. Stage peak efficiency of 0.834 was obtained at a weight flow of 26.4 kg/sec (58.3 lb/sec) and a pressure ratio of 1.581. The stall margin for the stage was 7.5 percent based on weight flow and pressure ratio at stall and peak efficiency conditions. The rotor minimum losses were approximately equal to design except in the blade vibration damper region. Stator minimum losses were less than design except in the tip and damper regions.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2904 , E-7081
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Spectrophotometric results from the Copernicus satellite. I - Instrumentation and performance. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The Princeton telescope-spectrometer on the OAO spacecraft Copernicus scans stellar spectra with a resolution of about 0.05 A between 950 and 1450 A, and twice this in first order between 1650 and 3000 A. The pointing during several minutes is steady within .02 sec, and the measured photometric precision in the shorter wavelength range is limited only by the statistics of photon counts, with 14-sec counts of about 1000 on an unreddened B1 star, m(v) = 5.0, at 1100 A. In the 1650-3000 A wavelength range, phototube noise resulting from cosmic rays makes observations difficult on stars fainter than m(v) = 3.0.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Astrophysical Journal; 181; May 1
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Analytical method for predicting the pressure distribution about a nacelle at transonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The formulation and development of a computer analysis for the calculation of streamlines and pressure distributions around two-dimensional (planar and axisymmetric) isolated nacelles at transonic speeds are described. The computerized flow field analysis is designed to predict the transonic flow around long and short high-bypass-ratio fan duct nacelles with inlet flows and with exhaust flows having appropriate aerothermodynamic properties. The flow field boundaries are located as far upstream and downstream as necessary to obtain minimum disturbances at the boundary. The far-field lateral flow field boundary is analytically defined to exactly represent free-flight conditions or solid wind tunnel wall effects. The inviscid solution technique is based on a Streamtube Curvature Analysis. The computer program utilizes an automatic grid refinement procedure and solves the flow field equations with a matrix relaxation technique. The boundary layer displacement effects and the onset of turbulent separation are included, based on the compressible turbulent boundary layer solution method of Stratford and Beavers and on the turbulent separation prediction method of Stratford.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2217
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of fin planform on the aerodynamic characteristics of a wingless missile with AFT cruciform controls at Mach 1.60, 2.36, and 2.86 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made in the Langley Unitary Plan wind tunnel to determine the effects of fin planform on the static longitudinal aerodynamic characteristics of a wingless maneuvering missile configuration having cruciform, all-movable, aft control surfaces. The tests were made at Mach numbers of 1.60, 2.36, and 2.86 through an angle of attack range from about -4 to 22 deg, at an angle of sideslip of 0 deg, and at a Reynolds number of 8.2 million based on model length. The pitch-control data were obtained at model roll angles of 0 and 45 deg. Control-surface forces and moments were also measured. Four alternate fin planforms were investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2774 , L-8783
    Format: application/pdf
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