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  • INSTRUMENTATION AND PHOTOGRAPHY  (148)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (130)
  • 1975-1979  (278)
  • 1
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    Measurements on the development of cascades in a tungsten-scintillator ionization spectrometer (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The response of a tungsten-scintillator ionization spectrometer to accelerated particle beams has been investigated. Results obtained from exposure of the approx. 1000 g/sq cm apparatus to 5, 10, and 15 GeV/c electrons and pions as well as to 2.1 GeV/nucleon C-12 and O-16 ions are presented. These results include cascade-development curves, fractions of the primary energy measured by the spectrometer, and resolutions of the apparatus for measuring the primary energies. For 15 GeV/c electrons, an average of about 82% of the incident energy is measured by the apparatus with resolution (normal standard deviation) of about 6%. For 15 GeV/c pions, an average of about 65% of the incident energy is measured with resolution of about 18%. The energy resolution improves with increasing energy and with increasing depth of the spectrometer.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nuclear Instruments and Methods; 126; 1975
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Spark calorimeter: An instrument for determining particle energy of cosmic radiation (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: In 1964 a spark calorimeter was installed at the NOR-Amberd Station (2000 m above sea level). The advantages of this calorimeter over the ionization calorimeter are illustrated.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (NASA-TT-F-807); p 349-354
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    ATS-6 - Flight performance of the Advanced Thermal Control Flight Experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Advanced Thermal Control Flight Experiment on ATS-6 was designed to demonstrate the thermal control capability of a thermal diode (one-way) heat pipe, a phase-change material for thermal storage, and a feedback-controlled heat pipe. Flight data for the different operational modes are compared to ground test data, and the performance of the components is evaluated on an individual basis and as an integrated temperature-control system.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    The Apollo 15 and 16 X-ray fluorescence experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An X-ray fluorescence spectrometer was flown aboard the Apollo 15 and 16 spacecrafts orbiting the moon. The X-ray instrument was used to produce a chemical map of that portion of the moon covered by the projected ground tracks and illuminated by the sun during the period of flight. The instrument includes three thin windowed proportional counters, two of which have selected X-ray filters. The field of view of the surface is determined by a collimator, while a detector on the opposite side of the spacecraft provides a continuous monitoring of the solar X-ray output. While the number of chemical elements determined was limited to Mg, Al, and Si, these proved to be very important diagnostic elements.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Space Science Instrumentation; 1; Aug. 197
    Format: text
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  • 5
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    High-resolution imaging X-ray detector (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The paper describes an X-ray detector using microchannel plates as a photocathode surface and imaging photoelectron multiplier, and a crossed wire grid as a two-dimensional position-sensitive detector. The position resolution is 10 microns. The crossed wire grid consists of 100-micron-diam wires on 200-micron centers. Position sensing is accomplished by electronic interpolation to 1/20 of the wire spacing. The quantum efficiency of the microchannel plates varies from 29% at 0.28 keV to 5% at 3 keV. This detector will provide second-of-arc X-ray imaging in the focal plane of the 342.9-cm focal length grazing-incidence telescope being prepared for the HEAO-B observatory. By addition of suitable photocathodes, it can be used for single-photon imaging light detection in the UV, visible, and near-IR-ranges. In all cases, it gives a very low dark counting rate, allows timing of individual events to 1 microsec or less, and can handle counting rates up to 10,000 per sec.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 47; Mar. 197
    Format: text
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  • 6
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    The dynamics and control of large flexible space structures. Part B: Development of continuum model and computer simulation (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The equations of motion of an arbitrary flexible body in orbit were derived. The model includes the effects of gravity with all its higher harmonics. As a specific example, the motion of a long, slender, uniform beam in circular orbit was modelled. The example considers both the inplane and three dimensional motion of the beam in orbit. In the case of planar motion with only flexible vibrations, the pitch motion is not influenced by the elastic motion of the beam. For large values of the square of the ratio of the structural modal frequency to the orbital angular rate the elastic motion was decoupled from the pitch motion. However, for small values of the ratio and small amplitude pitch motion, the elastic motion was governed by a Hill's 3 term equation. Numerical simulation of the equation indicates the possibilities of instability for very low values of the square of the ratio of the modal frequency to the orbit angular rate. Also numerical simulations of the first order nonlinear equations of motion for a long flexible beam in orbit were performed. The effect of varying the initial conditions and the number of modes was demonstrated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-156976
    Format: application/pdf
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  • 7
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    Simulation verification techniques study: Simulation performance validation techniques document (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques and support software for the efficient performance of simulation validation are discussed. Overall validation software structure, the performance of validation at various levels of simulation integration, guidelines for check case formulation, methods for real time acquisition and formatting of data from an all up operational simulator, and methods and criteria for comparison and evaluation of simulation data are included. Vehicle subsystems modules, module integration, special test requirements, and reference data formats are also described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-150933 , MDC-E1136
    Format: application/pdf
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  • 8
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    Dynamics of spinning spacecraft during the deployment of flexible boom (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The effect of flexibility on the dynamics of a spinning symmetrical spacecraft during the extension (or retraction) of boom-type appendages is treated by modeling the appendages as compound spherical pendula with varying lengths. Both boom stiffness and structural damping are included. For constant boom length the resulting linearized equations of motion contain periodic coefficients involving the spin frequency. A bounded transformation converts this system into a kinematically equivalent one (with only constant coefficients), whose stability is analyzed using the Kelvin-Tait-Chetaev theorem. The dynamics during extension is predicted by numerical simulation of the nonlinear equations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-489 , Structures, Structural Dynamics and Materials Conference; Apr 03, 1978 - Apr 05, 1978; Bethesda, MD
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    NASA TECHNICAL REPORTS
  • 9
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    Development and test of two flexible cryogenic heat pipes (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results are presented for a comprehensive test program directed toward determining the physical and thermal performance of two flexible cryogenic heat pipes that can provide a highly efficient thermal link between a detector and a space radiator or other cooling system in spacecraft applications. A 100-200 K high-power heat pipe is tested with methane at 100-140 K while a 15-100 K low-temperature pipe is designed for operation with nitrogen and oxygen and is optimized for oxygen in the range 75-90 K. Parametric performance and design tradeoff studies are carried out to determine the optimum geometry and materials for the container and wicking systems. A spiral multiwrap wick in conjunction with braided bellows appears to be a workable solution to the problem of developing highly flexible heat transport devices for cryogenic applications.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 76-478 , Thermophysics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
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  • 10
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    Sonic spark chambers for cosmic-ray experiments (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The sonic spark chamber provides an attractive high resolution hodoscope for low flux cosmic ray experiments. Spark position is determined by measurement of the time of flight of the sonic shock front from the spark position to a number of piezoelectric transducers placed at the periphery of the chamber. For each spark, four quantities must be determined: the spark coordinates, the sound velocity, and the spark 'size'. By over-determining the four parameters, high accuracy is possible. With eight sonic transducers, air-gap spark positions were measured with an error of less than 100 microns everywhere over a 1 sq m region.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: International Cosmic Ray Conference; Aug 15, 1975 - Aug 29, 1975; Munich
    Format: text
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