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  • INSTRUMENTATION AND PHOTOGRAPHY  (91)
  • SPACE VEHICLES  (41)
  • 1970-1974  (132)
  • 1974  (132)
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  • 1970-1974  (132)
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  • 1
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    A magnetic bubble domain flight recorder (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A feasibility model of an all-electronic bubble memory system has been constructed. It uses a small 60k bit bubble recorder consisting of 6 chips of 10k bits each mounted in three separate packages operating as a FIFO at a 150 KHz bubble data rate. In addition to serving as a direct tape recorder replacement, the bubble recorder can be programmed for random access to each individual chip for ranom block access operation or for self-checking or by-passing any malfunctioning memory chip. Read and write operations can be performed asynchronously from very low frequency up to basic recording field frequency. A large 50M bit prototype is planned.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A new magnetic spectrometer system for cosmic ray studies (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: The balloon flight prototype or a cosmic ray superconducting magnet experiment designed for operation on the Space Shuttle is described. The physical and operating parameters of the scintillation, Cerenkov, emulsion and multiwire proportional counters used in the system for charge and rigidity measurements is given as well as the on-board data handling procedures.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: International Cosmic Ray Conference; Aug 17, 1973 - Aug 30, 1973; Denver, CO
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A multiwire proportional counter system for high energy astrophysics (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: Resolution tests of multiwire proportional counter delay line readout systems are reported. The system is being developed at NASA/JSC for use in a large balloon borne magnet spectrometer. The system is ultimately intended for use in Space Shuttle missions. Tests of two different types of delay line and associated electronics carried out in minimum ionizing particle beams (accelerator and sea level cosmic ray) are reported. Resolution performance is shown to be strongly dependent on type of gas mixture and in the case of inclined events upon the propagation velocity of the delay line. The resolution performance achieved for magic gas chamber filling (100 um at normal incidence) is far superior to any other state of the art technique capable of being applied to large geometry factor systems.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: International Cosmic Ray Conference; Aug 17, 1973 - Aug 30, 1973; Denver, CO
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    NASA TECHNICAL REPORTS
  • 4
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    Raman scattering applied to hypersonic air flow (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Raman scattering technique was applied to measure the local static temperature and gas number density over a sharp-edge flat-plate model in a Mach 5 nozzle of the Langley nozzle test chamber with air as the test gas. The angle of attack varied from -5 to 15 deg, and the stagnation temperature varied from 317 to 442 K, with stagnation pressures ranging from 170 kN to 2.8 MN/sq m. The measured values of static temperature and density ranged from 60 to 100 K and from 0.03 to 0.8 kg/cu m, respectively. A comparison with calculated values based on static pressure measurements along the model shows that the Raman scattering technique is a viable measurement method in applications to high-speed three-dimensional flows.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Journal; 12; Aug. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The UCSD/MIT hard X-ray and low energy gamma ray experiment for HEAO-A (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An HEAO-A spacecraft is described which is scheduled for launch in April 1977 to survey the sky in the 0.15 keV to 10 MeV range of X-rays with improved sensitivity and angular resolution. The spectral and time variations of discrete sources, and the spectrum and isotropy of the diffuse component will be measured. A hard X-ray and low energy gamma ray experiment is described which will use as an array of seven (NaI)(Tl)/CsI(Na) phoswich detectors and eight large CsI(Na) shields. Detector events are pulse-height analyzed with a selectable time resolution of 0.1, 0.005, or 0.00002 sec. The instrument background is expected to be comprised of approximately equal parts of diffuse gamma rays entering the aperture, radioactive decay of spallation products, and gamma ray leakage through the shields. Detailed background predictions are presented, and sensitivity estimates indicate that the Crab nebula should be detected up to approximately 5 MeV. Approximate 1% isotropy limits for the diffuse component of cosmic gamma rays should be achieved, and its spectrum measured with improved precision.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ESRO The Context and Status of Gamma Ray Astronomy; p 177-184
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    NASA TECHNICAL REPORTS
  • 6
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    Instrumentation optimization in Fourier spectroscopy. I - Far infrared beam splitters (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Computations of the reflectivity, transmissivity, and efficiency properties for TE, TM, and T45 deg waves of far-infrared beam splitters and of the polarizations induced at both reflection and transmission are described. Effects of variations in the state of polarization, orientation, pointing accuracy, and wavelength of the incident light, as well as variations in refractive index and thickness of the beam splitters, are discussed. These results apply directly to Fourier interferometer-spectrometers. They can be used for optimizing the performance of these instruments. They indicate, in particular, that some advantages may be gained by the use of incident polarized light (angle of polarization smaller than about 45 deg or negative elliptical polarization) or light of large incidence angle (larger than approximately 60 deg) or both.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 13; Aug. 197
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    NASA TECHNICAL REPORTS
  • 7
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    Wide range multi-channel analog switch (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A ten-channel analog switch has been developed as a sample and shape circuit for signals used as inputs to a logarithmic pulse height recording system. The circuit employs a field effect transistor as the switching element. Switching transients are reduced to approximately 2 mV by adding to the gated signal an inverted transient generated by an identical circuit with no signal applied. The circuit is linear to 2% from 3 mV to 10 V.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nuclear Instruments and Methods; 121; 1974
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Development and testing of laser Doppler system components for wake vortex monitoring. Volume 1: Scanner development, laboratory and field testing and system modeling (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A servo-controlled range/elevation scanner for the laser Doppler velocimeter (LDV) was developed and tested in the field to assess its performance in detecting and monitoring aircraft trailing vortices in an airport environment. The elevation scanner provides a capability to manually point the LDV telescope at operator chosen angles from 3.2 deg. to 89.6 deg within 0.2 deg, or to automatically scan the units between operator chosen limits at operator chosen rates of 0.1 Hz to 0.5 Hz. The range scanner provides a capability to manually adjust the focal point of the system from a range of 32 meters to a range of 896 meters under operator control, or to scan between operator chosen limits and at rates from 0.1 Hz to 6.9 Hz. The scanner controls are designed to allow simulataneous range and elevation scanning so as to provide finger scan patterns, arc scan patterns, and vertical line scan patterns. The development and testing of the unit is discussed, along with a fluid dynamic model of the wake vortex developed in a laser Doppler vortex sensor simulation program.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-120466 , LMSC-HREC-TR-D390159-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Strain gauge ambiguity sensor for segmented mirror active optical system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A system is described to measure alignment between interfacing edges of mirror segments positioned to form a segmented mirror surface. It serves as a gauge having a bending beam with four piezoresistive elements coupled across the interfaces of the edges of adjacent mirror segments. The bending beam has a first position corresponding to alignment of the edges of adjacent mirror segments, and it is bendable from the first position in a direction and to a degree dependent upon the relative misalignment between the edges of adjacent mirror segments to correspondingly vary the resistance of the strain guage. A source of power and an amplifier are connected in circuit with the strain gauge whereby the output of the amplifier varies according to the misalignment of the edges of adjacent mirror segments.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of gaseous and solid simulated jet plumes on an 040A space shuttle launch configuration at m=1.6 to 2.2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of plume-induced flow separation and aspiration effects due to operation of both orbiter and the solid rocket motors on a 0.019-scale model of the launch configuration of the Space Shuttle Vehicle is determined. Longitudinal and lateral-directional stability data were obtained at Mach numbers of 1.6, 2.0, and 2.2 with and without the engines operating. The plumes exiting from the engines were simulated by a cold-gas jet supplied by an auxiliary 200-atm air supply system and solid-body plume simulators. The aerodynamic effects produced by these two simulation procedures are compared. The parameters most significantly affected by the jet plumes are pitching moment, elevon control effectiveness, axial force, and orbiter wing loads. The solid rocket motor (SRM) plumes have the largest effect on the aerodynamic characteristics. The effect of the orbiter plumes in combination with the SRM plumes is also significant. Variations in the nozzle design parameters and configuration changes can reduce the jet plume-induced aerodynamic effects.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-3032 , A-5212
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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