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  • INSTRUMENTATION AND PHOTOGRAPHY
  • SPACECRAFT PROPULSION AND POWER
  • 1980-1984  (379)
  • 1930-1934
  • 1980  (379)
  • 1
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    Studies of upper atmosphere motions by VHF backscatter (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 240-241
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  • 2
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    Halogen Occultation Experiment (HALOE) (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 236-237
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  • 3
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    Solar Mesosphere Explorer (SME) (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 238-239
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  • 4
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    Application Explorer Mission 2 (AEM 2), Stratospheric Aerosol and Gas Experiment (SAGE) (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 234-235
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  • 5
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    The Solar Backscatter Ultraviolet (SBUV) and Total Ozone Mapping Spectrometer (TOMS) experiment on Nimbus 7 (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 231
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  • 6
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    Stratospheric Aerosol Measurement 2 (SAM 2) (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 229-230
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  • 7
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    The Stratospheric and Mesospheric Sounder (SAMS) experiment on Nimbus 7 (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 232-233
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  • 8
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    Limb Infrared Monitor of the Stratosphere (LIMS) experiment (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 227-228
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  • 9
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    Spacelab payload definition: Cryogenic Limb-Scanning Interfermeter and Radiometer (CLIR) (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 221-223
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  • 10
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    Improved measurement and calibration for stratospheric trace species (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 148
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  • 11
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    Laboratory study of resonance fluorescence (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 130-131
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  • 12
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    Photoionization mass spectrometry (1980)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA, Washington Upper Atmosphere Res. Program; p 16
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  • 13
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    Recent assessment of the performance and accuracy of a chemiluminescent rocket sonde for upper atmospheric ozone measurements (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The chemiluminescent rocket ozonesonde utilizing rhodamine-B as a detector and self-pumping for air sampling has been improved. The instrument employs standard meteorological sounding systems and is the only technique available for routine nighttime ozone measurements above balloon altitudes. The chemiluminescent detector, when properly calibrated, is shown to be specific to ozone, stable, and of sufficient sensitivity for accurate measurements of ozone from about 65-20 km. An error analysis indicates that the measured ozone profiles have an absolute accuracy of about + or - 12% and a precision of about + or - 6%. Approximately 20 flights have been conducted for geophysical investigations, while additional flights were conducted with other rocket and satellite ozone soundings for comparisons. In general, these comparisons showed good agreement.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 51; Oct. 198
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  • 14
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    Circular-scan streak tube with solid-state readout (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A circular-scan streak tube designed for use in a laser ranging system is described. Electrostatic focusing is used between the photocathode and a microchannel plate, and electrons from the microchannel plate are proximity focused onto an output phosphor screen. Electron beam deflection is achieved by driving two orthogonal sets of deflection plate assemblies in phase quadrature at a frequency of 200 MHz. The light intensity in the output beam trace is measured by using a circular Reticon array of 720 photodiodes, which is fiber-optically coupled to the output phosphor screen of the tube. Sample measurements of frequency-doubled Nd:YAG laser-pulse waveforms are given. Also the output beamwidth has been measured at the 200-MHz deflection frequency. The results suggest a limiting resolution of 33 psec for the circular-scan streak tube used for these tests.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; Oct. 15
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  • 15
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    Oil film thickness measurement using airborne laser-induced water Raman backscatter (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The use of laser-induced water Raman backscatter for remote thin oil film detection and thickness measurement is reported here for the first time. A 337.1-nm nitrogen laser was used to excite the 3400-cm-1 OH stretch band of natural ocean water beneath the oil slick from an altitude of 150 m. The signal strength of the 381-nm water Raman backscatter was always observed to depress when the oil was encountered and then return to its original undepressed value after complete aircraft traversal of the floating slick. After removal of background and oil fluorescence contributions, the ratio of the depressed-to-undepressed airborne water Raman signal intensities, together with laboratory measured oil extinction coefficients, is used to calculate the oil film thickness.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; Oct. 1
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  • 16
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    Atmospheric laser Doppler velocimetry - An overview (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Research, development, and application of atmospheric laser Doppler velocimetry are overviewed. Consideration is given to operation principles of CO2 heterodyne systems. Global wind, pollution, V/STOL flow, and true airspeed measurements are outlined. Wind energy, dust devils, water spouts, tornadoes, and aircraft wake vortices are covered.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 19; July-Aug
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  • 17
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    Development of a pulsed 9.5 micron lidar for regional scale O3 measurement (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A pulsed infrared lidar system designed for application to the remote sensing of atmospheric trace gases from an airborne platform is described. The system is also capable of measuring the infrared backscatter characteristics of the ocean surface, terrain, cloud, and aerosol targets. The lidar employed is based on dual wavelength pulse energy measurements in the 9-11 micrometer wavelength region.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 19; July-Aug
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  • 18
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    Three-dimensional imaging of X-ray and gamma-ray objects in real time (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A simple device is described that is capable of providing real-time 3-D viewing of extended X-ray and gamma-ray objects. The visible-light images produced by the device are not merely stereoscopic, i.e., one perspective, but possess both horizontal and vertical parallax with a reasonably large field of view.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; Sept. 1
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  • 19
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    Grid polarizers for infrared Fourier spectrometers (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Infrared grid polarizers consisting of copper lines with a 3.6-micron grid constant on a 4-micron-thick Mylar polyester substrate have been prepared by the techniques of photolithography and sputter-etching. Their polarization properties have been measured and found to be suitable for use at infrared frequencies below 700/cm. The polarizers have been used to extend the useful frequency range of a Martin-Puplett polarizing interferometer designed for Fourier transform spectroscopy. The efficiency of the interferometer has been measured over a frequency range from 50 to 700/cm and compared to that of a conventional Michelson interferometer. The results are shown to be consistent with the measured properties of the polarizers. Methods are suggested for improving the efficiency of a Martin-Puplett interferometer which employs these polarizers.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Infrared Physics; 20; July 198
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  • 20
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    Absolute line strengths in nu4, /C-12/H4 - A dual-beam diode laser spectrometer with sweep integration (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A tunable diode laser spectrometer with several unique features has been developed for use in the middle IR. The all-reflective optical system has a dual-beam configuration before the dispersive mode selector to eliminate transit-angle errors at the calibration etalon. By maintaining separated beams through the mode selector, beam combiner losses are avoided. Averaging successive sweeps of the current-modulated laser permits stable reproducible spectral integrations, eliminating etalon thermal errors and producing high photometric sensitivity. Line strengths have been measured using this instrument for eleven transitions in nu4 of (C-12)H4. These include R0 and R1 and nine P-branch transitions in the 1202-1263-per cm range. Techniques for measuring strengths with a diode laser are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; Aug. 15
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  • 21
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    Sampling submicrometer particles suspended in near sonic and supersonic free jets (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Aerosols containing solid, spherical stearic acid particles with a mean diameter of 0.8 micron and a geometric standard deviation of 1.28 were sampled with small bore front-facing aspirating probes in near-sonic and supersonic unheated free jets. The results are compared to compute the sampling error associated with a high-speed jet sample.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Air Pollution Control Association; vol. 30
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  • 22
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    Measurement of the specific refractivities of CF4 and C2F6 (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: In order to relate the measured fringe shift of an interferometer to the density of a medium, the relation between density and refractive index, which is expressed by the specific refractivity, must be known. In the present paper, the specific refractivities of the wind tunnel test gases CF4 and C2F6 are determined in order to verify estimations based on the atomic refractivities of carbon and fluorine. A Twyman-Green two-beam interferometer with a 633-nm He-Ne laser light source was used to measure the specific refractivity as a function of fringe shift as the density of the gas was changed. Values of 0.122 and 0.131 cu cm/g were obtained for CF4 and C2F6 respectively at a temperature of 300 K, which are within 1% of the values computed from the atomic refractivities.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Chemical Physics; 73; July 15
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  • 23
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    Origin of reverse annealing in radiation-damaged silicon solar cells (1980)
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    Publication Date: 2011-08-17
    Description: The paper employs relative defect concentrations, energy levels, capture cross sections, and minority carrier diffusion lengths in order to identify the defect responsible for the reverse annealing observed in a radiation damaged n(+)/p silicon solar cell. It is reported that the responsible defect, with the energy level at +0.30 eV, has been tentatively identified as boron-oxygen-vacancy complex. In conclusion, it is shown that removal of this defect could result in significant cell recovery when annealing at temperatures well below the currently required 400 C.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Applied Physics Letters; 36; Apr. 15
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  • 24
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    Absorption coefficient instrument for turbid natural waters (1980)
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    Publication Date: 2011-08-17
    Description: The paper presents an instrument that directly measures multispectral absorption coefficient of turbid natural water. Attention is given to the design, which is shown to incorporate methods for the compensation of variation in the internal light source intensity, correction of the spectrally dependent nature of the optical elements, and correction for variation in the background light level. In addition, when used in conjunction with a spectrally matched total attenuation instrument, the spectrally dependent scattering coefficient can also be derived. Finally, it is reported that systematic errors associated with multiple scattering have been estimated using Monte Carlo techniques.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; May 15
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  • 25
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    HOE/lensless matched spatial filter wavelength-scaling correlator (1980)
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    Publication Date: 2011-08-18
    Description: A scaling correlator optical pattern recognition system is described in which a lensless matched spatial filter (with the second Fourier transform lens and the matched spatial filter recorded on the same plate) is used with a first Fourier transform lens that is also an holographic optical element. The matched spatial filter is recorded at one wavelength and correlation is obtained at a second wavelength. Experimental demonstration and output correlation SNR data are reported, together with a comparison of the system's noise level using conventional optics and holographic elements.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optics Communications; 34; Sept
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  • 26
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    Quantitative analysis of autoradiographic image intensification using Thiourea-S35 (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Photographic images enhanced by the method of Thiourea-S35 autoradiography are evaluated in terms of signal-to-noise ratio, detective quantum efficiency (DQE), and Wiener spectrum analysis using digitized images. It is determined that the original signal-to-noise ratio is not degraded by the intensification process which allows an increase in the practical working DQE as a function of density. These results apply at all spatial frequencies that were tested. The advantage given by autoradiography is the ability to produce usable images from emulsions originally exposed to the low densities corresponding to maximum DQE and movement of faint image densities above the level of the threshold for detection.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Astronomical Society of the Pacific; vol. 92
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  • 27
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    Aliasing and blurring in 2-D sampled imagery (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The quality of image reconstructions from discrete data suffers not only from the blurring of spatial detail caused by limitations in the spatial frequency response of electrooptical systems, but also from the aliasing generated if spatial detail has been undersampled. Previous studies have observed that reasonable spot intensity profiles and photosensor aperture shapes of equivalent size result in about equal blurring but that some profiles and shapes suppress aliasing better than others. This paper presents quantitative results of the magnitude of aliasing and blurring as a function of random radiance fields typical for natural scenes and of spatial responses and sampling intervals typical for TV cameras and optical-mechanical scanners. These results indicate that aliasing may often be a larger source of degradation than either blurring or electronic noise.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; July 1
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  • 28
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    Apparatus for trapping and thermal detection of atomic hydrogen in high magnetic fields at low temperatures (1980)
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    Publication Date: 2011-08-17
    Description: An apparatus is described in which hydrogen atoms were trapped at temperatures down to 1.1 K in the 11 T field of a large volume superconducting magnet. A high sensitivity thermal detector was used to study trapping and recombination of atoms on the detector surface. The apparatus permits the application of extremely high steady state magnetic fields to study the potential effects of electron spin polarization on the stabilization of hydrogen atoms.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 51; May 1980
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  • 29
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    Laser measurement of extinction coefficients of highly absorbing liquids (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A coaxial dual-channel laser system has been developed for the measurement of extinction coefficients of highly absorbing liquids. An empty wedge-shaped sample cell is first translated laterally through a He-Ne laser beam to measure the differential thickness using interference fringes in reflection. The wedge cell is carefully filled with the oil sample and translated through the coaxially positioned dye laser beam for the differential attenuation or extinction measurement. Optional use of the instrumentation as a single-channel extinction measurement system and also as a refractometer is detailed. The system and calibration techniques were applied to the measurement of two crude oils whose extinction values were required to complete the analysis of airborne laser data gathered over four controlled spills.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; Apr. 1
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  • 30
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    Laboratory investigations of cloud nuclei from combustion of Space Shuttle propellant (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Small quantities of solid rocket motor propellant, of the type to launch the Space Shuttle, were burned at ambient pressure in the laboratory to provide aerosol samples for characterization. A portion of each sample was injected into an isothermal cloud chamber and the remainder into a 770-liter holding tank. Portable ice nucleus (IN) counters, filter devices for IN determinations and a cloud condensation nucleus (CCN) counter sampled from the tank. The measurements show that particles resulting from the combustion of the propellant are active IN (3.3 times 10 to the 8th to 1.5 times 10 to the 11th/g active at 20 C). The portable counters and filters detected significantly fewer IN than the isothermal cloud chamber. The propellant aerosol is a prolific source of CCN that swamped the instrument.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Applied Meteorology; 19; Feb. 198
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  • 31
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    Nuclear Science Symposium, 26th and Symposium on Nuclear Power Systems, 11th, San Francisco, Calif., October 17-19, 1979, Proceedings (1980)
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    Publication Date: 2011-08-17
    Description: The paper covers the studies presented on nuclear science and nuclear power systems symposiums. The studies deal with nuclear radiation detectors, nuclear circuits and systems, space and medical instrumentation, as well as with environmental and reactor instrumentation. Data preprocessing and acquisition are discussed. Emphasis is placed on the engineered safety features of nuclear systems.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 32
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    Wall proximity corrections for hot-wire readings in turbulent flows (1980)
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    Publication Date: 2011-08-17
    Description: This note describes some details of recent (successful) attempts of wall proximity corrections for hot-wire measurements performed in a three-dimensional incompressible turbulent boundary layer. A simple and quite satisfactory method of estimating wall proximity effects on hot-wire readings is suggested.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: DISA Information; Feb. 198
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  • 33
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    Measurement of dielectric properties and determination of microwave emissivity of polluted waters (1980)
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    Publication Date: 2011-08-18
    Description: The dielectric properties of polluted waters are measured with a reflection-type resonant cavity at 1.43 GHz. Very small water samples in quartz tubes of known volume are placed in the center of the maximum electric field. Measurement of the resonance-frequency variation and a change of the cavity's quality factor are used to determine the dielectric properties. The microwave emissivity of the polluted water is then calculated via the Fresnel equation and applied to data reductions of microwave radiometer measurements.
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  • 34
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    Middle atmosphere NO/x/ production due to ion propulsion induced radiation belt proton precipitation (1980)
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    Publication Date: 2011-08-18
    Description: The suggestion that keV Ar(+) resulting from ion propulsion operations during solar power satellite construction could cause energetic proton precipitation from the inner radiation belt is examined to determine if such precipitation could cause significant increases in middle atmosphere nitric oxide concentrations thereby adversely affecting stratospheric ozone. It is found that the initial production rate of NO (mole/cu cm-sec) at 50 km is 130 times that due to nitrous oxide reacting with excited oxygen. However, since the time required to empty the inner belt of protons is about 1 sec and short compared to the replenishment time due to neutron decay, precipitation of inner radiation belt protons will have no adverse atmospheric environmental effect.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Solar Power Review; 1; 3, 19; 1980
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  • 35
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    Limits to the NEP of an intracavity LiNbO3 upconverter (1980)
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    Publication Date: 2011-08-17
    Description: Limits to low noise equivalent power (NEP) operation of a lithium niobate upconverter are investigated. Upconversion is achieved inside the optical cavity of an Ar-ion laser. Limits to NEP are imposed by limits to conversion efficiency and by noise present in the upconversion process. Conversion efficiency is limited by thermal effects in the lithium niobate. Thermally induced wedging, focusing, and aberrations are caused by the lithium niobate absorption at the 514.5-nm argon pump wavelength. The primary component of noise in the upconverter is due to upconversion of thermal radiation from the lithium niobate crystal. The lowest NEP, at a wavelength of 3.4 microns, achieved in this study was 8.9 x 10 to the -14th W/(Hz to the 1/2 power).
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  • 36
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    Some dynamic and time-averaged flow measurements in a turbine rig (1980)
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    Publication Date: 2011-08-17
    Description: Four types of sensors were used to make both dynamic and time-averaged flow measurements in a cold turbine rig to determine the magnitude of errors in time-averaged total-pressure measurement at a station 5 1/2 blade cords downstream from the rotor. The errors turned out to be negligible. The sensors and their intended use are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 37
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    Nonlinear optical processing with Fabry-Perot interferometers containing phase recording media (1980)
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    Publication Date: 2011-08-17
    Description: New techniques in nonlinear optical processing are explored, based on the operation of intensity level selection as performed by a Fabry-Perot interferometer containing a phase object. The image being processed is recorded on a medium between the mirrors as a spatially varying phase shift less than pi. The interferometer only transmits light through those portions of the object that corresponds to a single value of the phase and hence to a single intensity level in the input. More complicated operations such as thresholding and analog-to-digital conversion are performed by modulating the light source as the different levels are selected. Photoresist and lithium niobate have been used as phase objects, and experimental data for both are presented. Three kinds of Fabry-Perot interferometers have been used to demonstrate nonlinear processing using coherent and incoherent light. Color images have been produced with black and white inputs and white light illumination.
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  • 38
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    Digital recording acquisition subsystem for radio interferometry applications implementation plan (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The digital recording acquisition subsystem (DRAS) is a wideband digital recording system that can accommodate data sample rates from 0.125 to 8 MHz in binary increments. The implementation of the DRAS for radio interferometry applications in support of the Crustal Dynamics Project is described. The functional and performance characteristics of the equipment and the key aspects of the implementation plan are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Telecommun. and Data Acquisition Rept.; p 9-14
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    Laser beam manifold and particle photography system for use in fluid velocity measurements (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: A laser beam manifold and particle photography system has been developed for use in fluid velocity measurements. The laser manifold is a device which transforms a single laser beam into several uniform parallel beams. By orienting two manifolds mutually perpendicular, an optical grid can be formed which acts as a reference for fluid velocity measurements. This optical grid is for all practical purposes totally nonperturbing to the flow. Tracer particles moving in the plane of the grid are then photographed to yield fluid velocities that can be measured relative to the optical grid. System construction and theory are presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 51; Nov. 198
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    The Magsat precision vector magnetometer (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: This paper examines the Magsat precision vector magnetometer which is designed to measure projections of the ambient field in three orthogonal directions. The system contains a highly stable and linear triaxial fluxgate magnetometer with a dynamic range of + or - 2000 nT (1 nT = 10 to the -9 weber per sq m). The magnetometer electronics, analog-to-digital converter, and digitally controlled current sources are implemented with redundant designs to avoid a loss of data in case of failures. Measurements are carried out with an accuracy of + or - 1 part in 64,000 in magnitude and 5 arcsec in orientation (1 arcsec = 0.00028 deg).
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Johns Hopkins APL Technical Digest; 1; July-Sep
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    The Magsat scalar magnetometer (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The Magsat scalar magnetometer is derived from optical pumping magnetometers flown on the orbiting geophysical observatories. The basic sensor, a cross-coupled arrangement of absorption cells, photodiodes, and amplifiers, oscillates at the Larmor frequency of atomic moments precessing about the ambient field direction. The Larmor frequency output is accumulated digitally and stored for transfer to the spacecraft telemetry stream. In orbit the instrument has met its principal objective of calibrating the vector magnetometer and providing scalar field data.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Johns Hopkins APL Technical Digest; 1; July-Sep
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    Convolution of a Doppler line by a Gaussian instrument function (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A simple and direct method is obtained for assessing the distortion of a Doppler line by a Gaussian instrument function. It is suggested that a close approximation to the width of a Gaussian instrument function, or an almost Gaussian function, may be obtained by measuring a line with a Doppler absorption coefficient. The method is applicable to diode laser measurements, and may be used whenever a Gaussian instrument function is a reasonable approximation to real conditions
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Molecular Spectroscopy; 81; 1980
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    Liquid and solid propulsion system safety design criteria for space transportation system payloads (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Design safety criteria for Space Transportation System propulsion system payloads are discussed. Terms such as inhibit, monitoring, safing, safe distance, safe and arm device, and flow control device are defined and their use in design of safety requirements described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Washington The 1980 JANNAF Propulsion Systems Hazards Subcomm. Meeting, Vol. 1; p 37-41
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    Safety of liquid propulsion systems for STS payloads (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: STS payload safety requirements for Earth-storable liquid propulsion systems are reviewed with respect to applicable safety documents. The effect of normal flight and emergency landing/abort launch profiles on propulsion system design is delineated. Spacecraft studied include Earth satellites, interplanetary spacecraft, and orbit transfer vehicles. Safety considerations for monopropellant (hydrazine), bipropellant (nitrogen tetroxide/monomethyl hydrazine), and ion (mercury) propulsion systems are described. Safety requirements for specific components of propulsion systems are reported. Analysis techniques for STS payload fracture control requirements for pressure vessels and critical support structure are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Washington The 1980 JANNAF Propulsion Systems Hazards Subcomm. Meeting, Vol. 1; p 21-35
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    Space Telescope astrometry from CCD images (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The astrometric application of the Wide Field Camera and the Planetary Camera is reviewed. It is shown that the digital image centering algorithms can yield a positional accuracy of 0.1 milli-arcsecond. Deconvolution of CCD's sensitivity, non-flatness of the filters, and crinkling of the CCD surface may limit the positional accuracy of 1 milli-arcsecond.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 46
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    Performance of fused silica as a filter in a wide field-of-view earth radiation budget radiometer (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The thermal response of the fused silica dome filter in an earth radiation budget WFOV shortwave channel conceptual design and the impact of that response on the channel measurement, is described. Attention is given to results from design definition and performance analysis studies. Consideration is given to problems associated with achieving the desired levels of confidence in a high accuracy filtered earth radiation budget WFOV radiometer. Finally, design approaches, ground calibration, and data reduction techniques that minimize measurement uncertainties are covered.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; June 1
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  • 47
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    Hydrochloric acid aerosol and gaseous hydrogen chloride partitioning in a cloud contaminated by solid rocket exhaust (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Partitioning of hydrogen chloride between hydrochloric acid aerosol and gaseous HCl in the lower atmosphere was experimentally investigated in a solid rocket exhaust cloud diluted with humid ambient air. Airborne measurements were obtained of gaseous HCl, total HCl, relative humidity and temperature to evaluate the conditions under which aerosol formation occurs in the troposphere in the presence of hygroscopic HCl vapor. Equilibrium predictions of HCl aerosol formation accurately predict the measured HCl partitioning over a range of total HCl concentrations from 0.6 to 16 ppm.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Atmospheric Environment; 14; 5, 19; 1980
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    Design challenges of the thematic mapper (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper discusses the Thematic Mapper (TM), a multispectral earth resources sensor that will be launched on the Landsat-D satellite. The TM will operate in a circular, near-polar orbit of 750-km altitude and will scan a swath of earth 185 km wide. One TM mirror is a moving scan mirror, active during the forward and reverse scans; the final design of this component incorporates a mirror which has the required linearity and is not influenced by structural vibration. Another TM component that presented a design difficulty was the optical metering structure which has to be thermally stable across the temperature range in the instrument's orbital environment and duty cycle.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: IEEE Transactions on Geoscience and Remote Sensing; GE-18; Apr. 198
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  • 49
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    Ultrasonic spectrum analysis using frequency-tracked gated RF pulses (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: A new method of ultrasonic frequency analysis is introduced which employs frequency-tracked gated RF drive pulses rather than shock-excited broadband spikes to generate the ultrasonic waveform. The new technique, a variation of the sampled-continuous wave technique, eliminates problems associated with finite pulse widths of conventional methods. It is shown to yield correct ultrasonic wave velocity measurements of the sample irrespective of receiver gate width or position provided any portions of two successive echoes are gated simultaneously into the spectrum analyzer. The experimental observations are substantiated by a theoretical model based on the time-frequency domain formulation of ultrasonic frequency analysis.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Acoustical Society of America; vol. 67
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    Water depth measurement using an airborne pulsed neon laser system (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The paper presents the water depth measurement using an airborne pulsed neon laser system. The results of initial base-line field test results of NASA airborne oceanographic lidar in the bathymetry mode are given, with water-truth measurements of depth and beam attenuation coefficients by boat taken at the same time as overflights to aid in determining the system's operational performance. The nadir-angle tests and field-of-view data are presented; this laser bathymetry system is an improvement over prior models in that (1) the surface-to-bottom pulse waveform is digitally recorded on magnetic tape, and (2) wide-swath mapping data may be routinely acquired using a 30 deg full-angle conical scanner.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 19; Mar. 15
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    Performance of a flight qualified, thermoelectrically temperature controlled QCM sensor with power supply, thermal controller and signal processor (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A thermoelectrically temperature controlled quartz crystal microbalance (QCM) system was developed for the measurement of ion thrustor generated mercury contamination on spacecraft. Meaningful flux rate measurements dictated an accurately held sensing crystal temperature despite spacecraft surface temperature variations from -35 C to +60 C over the flight temperature range. An electronic control unit was developed with magentic amplifier transformer secondary power supply, thermal control electronics, crystal temperature analog conditioning and a multiplexed 16 bit frequency encoder.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center The 11th Space Simulation Conf.; p 257-268
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    Photovoltaic technology development for synchronous orbit (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Accomplishments and expected benefits are summarized for the following efforts: (1) achieving silicon solar cell efficiency of 18% at 200 micron m to 250 micron m thickness; (2) reducing silicon cell radiation damage in geosynchronous orbit after 10 years to less than 15%; (3) demonstrating coplanar back contact 50 micron m thick silicon solar cells with efficiency of 14%; (4) demonstrating the feasibility of a radiation tolerant GaAs concentrator cell; (5) achieving 30% efficient photo conversion in the laboratory; (6) defining candidate concepts for 50% efficient electromagnetic conversion; and (7) demonstrating the technology for protecting arrays capable of 300W/kg after 10 years in geosynchronous orbit.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Synchronous Energy Technol.; p 45-56
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    Noise adding radiometer performance analysis (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The DSN noise adding radiometer (NAR) measurement accuracy is analyzed. The NAR capability is part of the precision power monitor function recently introduced in the DSN. The potential system noise temperature measurement accuracy is estimated to be about 1.5% with the 1 kelvin noise diode. Performance verification requires comparison noise temperature measurements with the manual Y factor method and routine monitoring of critical elements in the NAR system such as system linearity and noise diode calibration. A technique is presented to calibrate and reduce the effects of the receiving system nonlinearity. Unsatisfactory performance or degradation of these critical NAR elements would require appropriate system upgrading.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Telecommun. and Data Acquisition Rept.; p 98-106
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    Synchronous energy technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The power program in NASA and DOD are discussed with emphasis on the technology for future large space power systems. The structure of the synchronous energy technology program is described and the technologies required for future geosynchronous power stations are defined. The output of the program is to be a series of design data documents to provide design information and to transfer the technology to the involved community.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Synchronous Energy Technol.; p 1-7
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    Advanced concepts (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The relative strengths of those interactions which enable propulsive forces are listed as well as the specific impulse of various propellants. Graphics show the linear synchronous motor of the mass driver, the principle of the direct current electromagnetic launcher, and the characteristics of the rail gun.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 337-342
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    Electric propulsion for SPS (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design and characteristics of the solar power satellite electric propulsion system are described. Both the payload powered orbital transfer vehicle and the independent powered transfer vehicle configuations are discussed. Mass estimates for the system, the average cost per system unit, and the cost per flight estimates are also given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 229-236
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    Effect of orbital transfer loads on large platforms (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A preliminary automated structural sizing procedure suitable for conceptual design and early tradeoff studies of large truss platforms configured for shuttle transportation to LEO is discussed as well as some orbital transfer design considerations. Platforms that are sized to withstand orbital transfer loads for the LEO to GEO maneuver are compared to platforms sized only for LEO application. It is concluded that for platforms supporting low mass distributed payloads, platform and strut frequency requirements are strong design drivers for LEO applications. The struts are found to be extremely slender, thinswalled, and of small diameter. If full advantage is to be taken of these minimum mass designs, a manufacturing capability must be developed for long straight struts. For platforms that are to be transferred from LEO to GEO in a deployed state, the orbital transfer loads become design drivers. However, even for an initial thrust-to-weight ratio equal to 0.1, a platform on the order of 100 m diameter appears packageable with its OTV in one shuttle flight, and larger platforms appear possible at lower thrust-to-weight ratios.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 143-155
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    Status of nickel-hydrogen cell technology (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Nickel hydrogen cell technology has been developed which solves the problems of thermal management, oxygen management, electrolyte management, and electrical and mechanical design peculiar to this new type of battery. This technology was weight optimized for low orbit operation using computer modeling programs but is near optimum for other orbits. Cells ranging in capacity up to about 70 ampere-hours can be made from components of a single standard size and are available from two manufacturers. The knowledge gained is now being applied to the development of two extensions to the basic design: a second set of larger standard components that will cover the capacity range up to 150 ampere-hours; and the development of multicell common pressure vessel modules to reduce volume, cost and weight. A manufacturing technology program is planned to optimize the producibility of the cell design and reduce cost. The most important areas for further improvement are life and reliability which are governed by electrode and separator technology.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 97-105
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    The table mountain 8-mm-wavelength interferometer (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The system components, performance, and calibration of two element radio interferometer operating at 8.33 mm wavelength are discussed. The interferometer employs a 5.5 m and a 3 m diameter antenna on an east-west baseline of 60 or 120 m, yielding fringe spacings at transit of 28 or 14 in. respectively. The broad intermediate frequency bandpass of 100 to 350 MHz and the system noise temperature of 500 K provide high sensitivity for the measurement of continuum sources. The interferometer has been used for high resolution studies of the planets and the Sun, and it is currently being adapted to study solar flare emissions at high spatial and time resolution.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Telecommun. and Data Acquisition Rept.; p 1-8
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    Influence of interorbit acceleration on the design of large space antennas (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The characteristics of the acceleration-induced loading in structures consisting of triangular lattices are investigated and some initial quantitative results on the effect on the design mass and stowage volume are presented. The approach used defines the structural design that would be used if no interorbit acceleration were required and then determines what strengthening would be required to accommodate the loads due to acceleration. The basic zero acceleration design can be based on the stringent accuracy requirements placed on the antennas.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 157-178
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    Large space systems technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Technical challenges of shuttle-era large space systems include the development of space-configured spacecraft concepts, compatibility with the space transportation system, and cost effectiveness. The objectives and organization of NASA's large space structures program are outlined and program elements are discussed. The technology for the offset wrap-rip and the maypole (hoop/column) antenna concepts are discussed as well as analysis techniques for predicting the electromagnetic performance of a broad class of large reflectors. Deployable systems, assembly methods, and modular control systems for space platforms are described. Assembly equipment and devices, surface sensors and shape control, control and stabilization, and integrated analysis and design are also considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 9-22
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    Spacelab energetic ion mass spectrometer (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Basic design criteria are given for an ion mass spectrometer for use in studying magnetospheric ion populations. The proposed instrument is composed of an electrostatic analyzer followed by a magnetic spectrometer and simultaneously measures the energy per unit and mass per unit charge of the ion species. An electromagnet is used for momentum analysis to extend the operational energy range over a much wider domain than is possible with the permanent magnets used in previous flights. The energetic ion source regions, ion energization mechanisms, field line tracing, coordinated investigations, and orbit considerations are discussed and operations of the momentum analyzer and of the electrostatic energy analyzer are examined.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Marshall Space Flight Center Space Plasma Phys. Active Expt.; p 91-106
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    IUS solid rocket motor contamination prediction methods (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A series of computer codes were developed to predict solid rocket motor produced contamination to spacecraft sensitive surfaces. Subscale and flight test data have confirmed some of the analytical results. Application of the analysis tools to a typical spacecraft has provided early identification of potential spacecraft contamination problems and provided insight into their solution; e.g., flight plan modifications, plume or outgassing shields and/or contamination covers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center The 11th Space simulation Conf.; p 243-256
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    Electrochemical Orbital Energy Storage (ECOES) technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The versatility and flexibility of a regenerative fuel cell power and energy storage system is considered. The principal elements of a Regenerative Fuel Cell System combine the fuel cell and electrolysis cell with a photovoltaic solar cell array, along with fluid storage and transfer equipment. The power output of the array (for LEO) must be roughly triple the load requirements of the vehicle since the electrolyzers must receive about double the fuel cell output power in order to regenerate the reactants (2/3 of the array power) while 1/3 of the array power supplies the vehicle base load. The working fluids are essentially recycled indefinitely. Any resupply requirements necessitated by leakage or inefficient reclamation is water - an ideal material to handle and transport. Any variation in energy storage capacity impacts only the fluid storage portion, and the system is insensitive to use of reserve reactant capacity.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 81-95
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    Air Force space power technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The military spacecraft power subsystem design requirements, developments goals, and planned technology efforts are summarized. The mission drivers of performance (weight and volume), hardening (survivability), autonomy, reliability, and miniaturization influence space mission effectiveness are outlined. The anticipated performance versus power level trends for reactor static conversion systems are illustrated. A conceptual design for a space based radar system is also given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 15-28
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    Low-thrust chemical propulsion (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results from investigations leading to the definition of low thrust chemical engine concepts are described. From the thrust chamber cooling analyses, regenerative/radiation-cooled LO2/H2 thrust chambers offered the largest thrust and chamber pressure operational envelope primarily due to the superior cooling capability of hydrogen and its low critical pressure. Regenerative/radiation-cooled LO2/CH4 offered the next largest operational envelope. The maximum chamber pressure for film/radiation-cooling was significantly lower than for regenerative/radiation-cooling. As in regeneration-cooling, LO2/H2 thrust chambers achieved the highest maximum chamber pressure, LO2/CH4 film/radiation-cooling was found not feasible and LO2/RP-1 film/radiation-cooling was extremely limited. In the engine cycle/configuration evaluation, the engine cycle matrix was defined through the incorporation of the heat transfer results. Engine cycle limits were established with the fuel-cell power cycle achieving the highest chamber pressure; however, the fuel cell system weights were excessive. The staged combustion cycle achieved the next highest chamber pressure but the preburner operational feasibility was in question.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 263-286
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    Low-thrust vehicle concept studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Part of NASA's orbit transfer vehicle propulsion program is devoted to the development of analytical tools to define propulsion system performance, weight, size, and other parameters, and to develop packing concepts for LSS mission propulsion and payload systems. Packing studies discussed relate to shuttle cargo bay constraints; low thrust engine profile and performance; large space frame concept and weight; low thrust vehicles stowed in shuttle, LSS payload capability, and weight distribution. Further study is needed to determine interactions among propulsion system, payload structures, and shuttle. Low thrust-to-weight ratios are desirable to maximize payload weights and deployed areas.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 97-106
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    The WISP/HF system for Spacelab (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The high frequency part of the waves in space plasmas system, WISP/HF, is a flexible shuttle Spacelab instrument for transmitting, receiving, and processing signals in the 0.3 to 30 MHz range. It permits a wide range of plasma wave experiments in the ionosphere including studies of the transmitting antenna, fundamentals of electromagnetic (EM) and electrostatic (ES) waves in magnetoplasmas, instabilities and nonlinearities, and remote sounding of ionospheric structure. Collaborative investigations involving other WISP equipment (e.g., antenna and propagation studies with the WISP/VLF system) or other Spacelab facilities (e.g., beam plasma interactions using charged particle guns) are envisaged. A few specific examples illustrate the relevance of WISP/HF to current scientific interest. The overall goal is to help build a comprehensive understanding of plasmaspheric wave physics through group studies.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Marshall Flight Center Space Plasma Phys. Active Expt.; p 173-184
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    Power management (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The multihundred kW power system management and a distribution program aims to develop critical components, circuits, and subsystems required to manage the generation, storage, and distribution of energy in large, orbital space systems. To accomplish this objective, a reference system including subsystems for the generation and storage of energy and management of electrical and thermal energy was designed and is being used to assess at the system level the impact of changing various subsystem parameters. A power management subsystem will then be designed. The subsystem is autonomous and based on ground utility systems concepts to the maximum extent possible. An agency power system breadboard is under development for characterizing and verifying the various component and subsystem technology developments.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 107-114
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    Large solar arrays (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A spectrophotovoltaic converter, a thermophotovoltaic converter, a cassegrainian concentrator, a large silicon cell blanket, and a high flux approach are among the concepts being investigated as part of the multihundred kW solar array program for reducing the cost of photovoltaic energy in space. These concepts involve a range of technology risks, the highest risk being represented by the thermophotovoltaics and spectrophotovoltaics approaches which involve manipulation to of the incoming spectrum to enhance system efficiency. The planar array (solar blanket) has no technology risk and a moderate payback. The primary characteristics, components, and technology concerns of each of these concepts are summarized. An orbital power platform mission in the late 1980's is being used to allow a coherent technology advancement program in order to achieve a ten year life with maintenance at a capital recurring cost of $30/watt based on 1978 dollars.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 57-68
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    Electric propulsion and power (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The development of electric propulsion systems is discussed and the benefits of these systems to various space mission requirements are outlined. The characteristics and development status of 8 and 30 cm mercury ion thrusters and solar electric propulsion systems are reported. In addition the advantages of an inert gas thruster for Earth orbital missions are examined and include its capability for operation at higher values of specific impulse, the ease at which it can be integrated with space systems, and it's low pollution potential.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 219-228
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    Chemical propulsion technology (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An overview of NASA's low thrust liquid chemical propulsion program is presented with particular emphasis on thrust system technology in the ten to one thousand pound thrust range. Key technology issues include high performance of cooled low thrust engines; small cryogenic pumps; multiple starts-shutdowns (10) with slow ramps (approximately 10 seconds); thrust variation - 4/1 in flight and 20/1 between flights; long life (100 hours); improved system weight and size; and propellant selection.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 31-36
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    Solid-propellant rocket motor internal ballistics performance variation analysis, phase 5 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of research aimed at improving the predictability of internal ballistics performance of solid-propellant rocket motors (SRM's) including thrust imbalance between two SRM's firing in parallel are presented. Static test data from the first six Space Shuttle SRM's is analyzed using a computer program previously developed for this purpose. The program permits intentional minor design biases affecting the imbalance between any two SMR's to be removed. Results for the last four of the six SRM's, with only the propellant bulk temperature as a non-random variable, are generally within limits predicted by theory. Extended studies of internal ballistic performance of single SRM's are presented based on an earlier developed mathematical model which includes an assessment of grain deformation. The erosive burning rate law used in the model is upgraded and made more general. Excellent results are obtained in predictions of the performances of five different SRM's of quite different sizes and configurations. These SRM's all employ PBAN type propellants with ammonium perchlorate oxidizer and 16 to 20% aluminum except one which uses carboxyl terminated butadiene binder. The only non-calculated parameters in the burning rate equations that are changed for the different SRM's are the zero crossflow velocity burning rate coefficients and exponents. The results, in general, confirm the importance of grain deformation. The improved internal ballistic model makes practical development of an effective computer program for application of an optimization technique to SRM design which is also demonstrated. The program uses a pattern search technique to minimize the difference between a desired thrust-time trace and one calculated based on the internal ballistic model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-177145 , NAS 1.26:177145
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    A polarimeter for the high resolution ultraviolet spectrometer/polarimeter (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design requirements of the polarimeter were established by the scientific optical objectives of the experiment to be launched aboard the Solar Max Mission which will study active solar regions. The polarization of the light is accomplished by a rotating magnesium fluoride quarter wave plate. The quarter wave plates are rotated in 22 1/2 degree steps about an axis coincidental with the light beam. As the light beam passes through the wave plate, the transformation that occurs can be expressed by mathematical equations. By having the wave plates calibrated, the data obtained from solar flares can be analyzed and meaningful information provided to the investigators. The polarimeter has two wave plates with different optical characteristics to provide both redundancy and versatility. A four mirror polarizer was added behind one wave plate to provide additional polarization. The mechanical design, testing, and operation of the polarimeter for the high resolution ultraviolet spectrometer/polarimeter are described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Langley Res. Center Proc. of the 14th Aerospace Mech. Symp.; p 303-310
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    Electric propulsion technology (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The advanced electric propulsion program is directed towards lowering the specific impulse and increasing the thrust per unit of ion thruster systems. In addition, electrothermal and electromagnetic propulsion technologies are being developed to attempt to fill the gap between the conventional ion thruster and chemical rocket systems. Most of these new concepts are exagenous and are represented by rail accelerators, ablative Teflon thrusters, MPD arcs, Free Radicals, etc. Endogenous systems such as metallic hydrogen offer great promise and are also being pursued.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 23-30
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    Design and development of the quad redundant servoactuator for the space shuttle solid rocket booster thrust vector control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design and theory of operation of the servoactuator used for thrust vector control of the space shuttle solid rocket booster is described accompanied by highlights from the development and qualification test programs. Specific details are presented concerning major anomalies that occurred during the test programs and the corrective courses of action pursued.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center Proc. of the 14th Aerospace Mech. Symp.; p 125-141
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    Wide angle Michelson Doppler imaging interferometer (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The optical system, stepping control, phase and modulation depth, array detector, and directions sensor are described for a specialized type of Michelson interferometer which works at sufficiently high resolution to measure the line widths and Doppler shifts of naturally occurring atmospheric emissions. With its imaging capability, the instrument can potentially supply this data independently for each element of the 100 x 100 detector array. The experiment seeks: (1) to obtain vertical profiles of atmospheric winds and temperatures as functions of latitude by observing near the limb; (2) to acquire exploratory wind and temperature data on smaller scale structures in airglow irregularities and in auroral forms; and (3) to collaborate with other Spacelab experiments, such as barium cloud releases, in providing wind and temperature data.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Marshall Flight Center Space Plasma Phys. Active Expt.; p 75-90
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    Magnetospheric multiprobes: Investigations and instrumentation (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The multiprobe scientific objectives are to: (1) determine the spatial structure of plasma phenomena such as the aurora, convection reversals, and ion troughs; (2) separate spatial and temporal variations in these phenomena; (3) determine field aligned current densities; (4) perform multiple point analysis of particle beams, wave fields, and plasma clouds that are injected into the ionosphere and magnetosphere by Spacelab active experiment facilities. Trade studies described include: instrument accommodations, power, attitude determination, electric field antennas, storage and ejection, thermal control, tracking communications, command and data management, payload and mission specialist support, functional objectives, and orbital analysis.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Marshall Space Flight Center Space Plasma Phys. Active Expt.; p 185-214
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    P78-2 (SCATHA) satellite thermal balance test, a laboratory test (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Space simulation test programs can be carried out with a high probability of being troublefree with a competent staff, a well-maintained test facility and attention to interfaces; however, full-up thermal balance tests using the solar simulator, temperature control of infrared sources, the gimbal, a large number of thermocouples, and other requirements for a high fidelity thermal balance are still a challenge. The P78-2 (Scatha) satellite was successfully tested with one interruption and a four-day abbreviated retest to verify a modification. This was accomplished in spite of the new test crew, a facility beset with several operational problems, and marginal interface control. These problems were addressed with very good results. Subsequent tests have been highly successful.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Johnson Space Center The 11th Space Simulation Conf.; P 298-304
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    LSS/propulsion interactions studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Interactions between the LSS and the propulsion system are large, significant, interrelated, and complex. Issues and problems in interfacing include the effects on the structure from static, dynamic, and launch loads, control, thrust distribution, throttling, and the environment. Control interaction, the disposal of debris/obsolete spacecraft, and the constraints of launch to low Earth orbit must also be considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 37-52
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    Low-thrust vehicles concept studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Low thrust chemical (hydrogen-oxygen) propulsion systems configured specifically for low acceleration orbit transfer of large space systems were studied in order to provide the required additional data to better compare new, low thrust chemical propulsion systems with other propulsion approaches such as advanced electric systems. Study results indicate that it is cost-effective and least risk to combine the low thrust OTV and stowed spacecraft in a single 65 K shuttle. Mission analysis indicates that there are 25 such missions, starting in 1987. Multiple shuttles (LSS in one, OTV in another) result in a 20% increase in LSS (SBR) diameter over single shuttle launches. Synthesis and optimization of the LSS characteristics and OTV capability resulted in determination of the optimum thrust-to-weight and thrust level. For the space based radar with radial truss arms (center thrust application), the optimum thrust-to-weight (maximum) is 0.1, giving a thrust of 2000 lb. For the annular truss (edge-on thrust application) the structure is not as sensitive, and thrust of 1000 lb appears optimum. For the geoplatform, optimum T/W is .15 (3000 lb thrust). The effects of LSS structure material, weight distribution, and unit area density were evaluated, as were the OTV engine thrust transient and number of burns.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 73-96
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    Results of tests on a specimen of the SRB aft skirt heat shield curtain in the MSFC LRLF (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A full scale segment of the actual Solid Rocket Booster aft skirt heat shield curtain was tested in the Large Radiant Lamp Facility (LRLF) at Marshall Space Flight Center. The curtain was mounted in the horizontal position in the same manner as it is to be mounted on the SRB. A shaker rig was designed and used to provide a motion of the curtain, simulating that to be caused in flight by vehicle acoustics. Thermocouples were used to monitor curtain materials temperatures. Both ascent and reentry heat loads were applied to the test specimen. All aspects of the test setup performed as expected, and the test was declared successful.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170883 , NAS 1.26:170883 , LMSC-HREC-TM-D697896
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    GSFC specification electronic data processing magnetic recording tape (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design requirements are given for magnetic oxide coated, electronic data processing tape, wound on reels. Magnetic recording tape types covered by this specification are intended for use on digital tape transports using the Non-Return-to-Zero-change-on-ones (NRZI) recording method for recording densities up to and including 800 characters per inch (cpi) and the Phase-Encoding (PE) recording method for a recording density of 1600 cpi.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-80599 , NAS 1.15:80599
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    Apparatus and method for destructive removal of particles contained in flowing fluid (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An apparatus and method for destructively removing particles from a flowing gas containing the particles is described. In the specific embodiments disclosed the apparatus is adapted to remove carbon particles from diesel engine exhaust products. The exhaust products are directed to a predetermined location where they are rapidly vaporized and combine with oxygen in the exhaust products to form carbon dioxide. Vaporization in one embodiment is effected by a discharge grid located within an exhaust conduit, the grid being chosen so that alternate conductors defining the grid are spaced apart a distance approximately 125 times the mean diameter of the particles to be removed. A voltage differential of approximately 690 volts is applied across adjacent conductors.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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    Retrofit and verification test of a 30-cm ion thruster (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Twenty modifications were found to be necessary and were approved by design review. These design modifications were incorporated in the thruster documents (drawings and procedures) to define the J series thruster. Sixteen of the design revisions were implemented in a 900 series thruster by retrofit modification. A standardized set of test procedures was formulated, and the retrofit J series thruster design was verified by test. Some difficulty was observed with the modification to the ion optics assembly, but the overall effect of the design modification satisfies the design objectives. The thruster was tested over a wide range of operating parameters to demonstrate its capabilities.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165233
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    Self-calibrating threshold detector (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A self calibrating threshold detector comprises a single demodulating channel which includes a mixer having one input receiving the incoming signal and another input receiving a local replica code. During a short time interval, an incorrect local code is applied to the mixer to incorrectly demodulate the incoming signal and to provide a reference level that calibrates the noise propagating through the channel. A sample and hold circuit is coupled to the channel for storing a sample of the reference level. During a relatively long time interval, the correct replica code provides an output level which ranges between the reference level and a maximum level that represents incoming signal presence and synchronism with the replica code. A summer substracts the stored sample reference from the output level to provide a resultant difference signal indicative of the acquisition of the expected signal.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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    Specifying and calibrating instrumentations for wideband electronic power measurements (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The wideband electric power measurement related topics of electronic wattmeter calibration and specification are discussed. Tested calibration techniques are described in detail. Analytical methods used to determine the bandwidth requirements of instrumentation for switching circuit waveforms are presented and illustrated with examples from electric vehicle type applications. Analog multiplier wattmeters, digital wattmeters and calculating digital oscilloscopes are compared. The instrumentation characteristics which are critical to accurate wideband power measurement are described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-81545 , DOE/NASA/1044-8
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    Low cost cryostat (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A cryostat for use in a low or a substantially gravity-free environment adapted to cool an experiment through the use of helium 2, or helium in its super fluid state is characterized by a number of interchangeable daughter dewars and helium supply or mother dewar. A low pressure venting system is provided for converting helium contained in the mother dewar to a superfluid state for use as a primary cryogen. Each daughter dewar is adapted to be removably mounted in mated relation on the mother dewar and is characterized by support for an experiment package, a source of helium to be employed as a secondary cryogen. A heat pipe is suspended from each daughter dewar and adapted to be extended into the mother dewar for facilitating cooling of the secondary cryogen. A transfer of heat from the package to the primary cryogen, via the secondary cryogen, is accommodated as a film flow of helium 2 progresses from the heat pipe to the experiment dewar.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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    Orbit Transfer Vehicle (OTV) advanced expander cycle engine point design study. Volume 2: Study results (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Detailed computer models of the engine were developed to predict both the steady state and transient operation of the engine system. Mechanical design layout drawings were prepared for the following components: thrust chamber and nozzle; extendible nozzle actuating mechanism and seal; LOX turbopump and boost pump; hydrogen turbopump and boost pump; and the propellant control valves. The necessary heat transfer, stress, fluid flow, dynamic, and performance analyses were performed to support the mechanical design.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-161638 , REPT-33574-F-VOL-2
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    Evaluation of space shuttle main engine fluid dynamic frequency response characteristics (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to determine the POGO stability characteristics of the space shuttle main engine liquid oxygen (LOX) system, the fluid dynamic frequency response functions between elements in the SSME LOX system was evaluated, both analytically and experimentally. For the experimental data evaluation, a software package was written for the Hewlett-Packard 5451C Fourier analyzer. The POGO analysis software is documented and consists of five separate segments. Each segment is stored on the 5451C disc as an individual program and performs its own unique function. Two separate data reduction methods, a signal calibration, coherence or pulser signal based frequency response function blanking, and automatic plotting features are included in the program. The 5451C allows variable parameter transfer from program to program. This feature is used to advantage and requires only minimal user interface during the data reduction process. Experimental results are included and compared with the analytical predictions in order to adjust the general model and arrive at a realistic simulation of the POGO characteristics.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-161614 , WYLE-TM-80-8
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    Evaluation of axial lock-up of space shuttle main engine bearings from high pressure oxygen turbopump (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The mainshaft support bearings of long life turbopumps for use on the space shuttle were evaluated to determine possible causes of failure. Specific aspects examined include the sensitivity of 15 degree versus 25 degree contact angle bearings with regard to heat damage and thermal runaway, the L/D aspects of the turbine end bearing pair with regard to hang-up due to cocking, the hang-up required to support a 44.5 KN axial load without cartridge slipping, the outer race growth as a result of a 44.5 KN axial load, and bearing torque as a function of axial load. Results indicate that hang-up of the cartridge due to bearing heating is a serious problem especially if poor lubrication of the bearing occurs and that race growth due to axial load can contribute to cartridge lock-up. The experimental evaluation of bearing performance under axial loads indicates that the bearing torque is a strong function of surface lubrication.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-161613
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    Design Studies for a Far Infrared Absolute Spectrometer for the Cosmic Background Explorer (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Unrelenting symmetry of design is required to assure the thermal balance of a cryogenically cooled, rapid scan interferometer spectrometer to be mounted in vacuum with the Cosmic Background Explorer liquid helium dewar. The instrument receives inputs from Winston cone optical flux collectors, one open to space and a second coupled to a black body reference source. A differential instrument, the spectrometer produces outputs corresponding to the Fourier transform of the spectral radiance difference between the two inputs. The two outputs are sensed by four detectors, two optimized for shorter wavelength response, and two optimized for longer wavelengths. The optical design, detector and signal channel, system sensitivity, mechanics, thermal control and cryogenics, electronics and power systems, command and control, calibration, system test requirements, and the instrument interface are discussed. Recommendations for continued work are indicated for the superconducting reflective horns, the motor bearing and drive, and design detail.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-160051 , BE-79-808
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    Orbit Transfer Vehicle (OTV) engine phase A study, extension 1. Volume 3: Study cost estimates (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Program cost and planning data based on 1980 technology and shown in 1979 dollars for a 20K lb Thrust Staged Combustion Cycle Engine are presented. These data were compared with those for the Advanced Expander Cycle Engine at 10K lb and 20K lb thrust levels.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-161608 , REPT-32999-F-E1-VOL-3
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    Determination of optimum voltages of ion focusing devices using computer techniques (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Electric potentials for two dimensional cross sections of ion focusing devices used in a mass spectrometer are calculated via a series of computer programs designed to compute potentials between areas of fixed voltages. Ion trajectories within these devices may be determined by computer and a histogram obtained which plots ion density against ion position along a plate of the focusing device. For each lens system, a plate voltage may be changed, the electric potentials recalculated, and a new histogram calculated in order to determine if the new voltage configuration has increased the device's efficiency. This process may be repeated until the optimum voltage values have been found for maximum particle transmission in each focusing device.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-163730
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    Outer planet investigations using a CCD camera system (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Problems related to analog noise, data transfer from the camera buffer to the storage computer, and loss of sensitivity of a two dimensional charge coupled device imaging system are reported. To calibrate the CCD system, calibrated UBV pinhole scans of the Saturn disk were obtained with a photoelectric area scanning photometer. Atmospheric point spread functions were also obtained. The UBV observations and models of the Saturn atmosphere are analyzed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-163704
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    Space Transportation System solid rocket booster thrust vector control system (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Solid Rocket Booster, Thrust Vector Control (TVC) system was designed in accordance with the following requirements: self-contained power supply, failsafe operation, 20 flight uses after exposure to seawater landings, optimized cost, and component interchangeability. Trade studies were performed which led to the selection of a recirculating hydraulic system powered by Auxiliary Power Units (APU) which drive the hydraulic actuators and gimbal the solid rocket motor nozzle. Other approaches for the system design were studied in arriving at the recirculating hydraulic system powered by an APU. These systems must withstand the imposed environment and be usable for a minimum of 20 Space Transportation System flights with a minimum of refurbishment. The TVC system completed the required qualification and verification tests and is certified for the intended application. Substantiation data include analytical and test data.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-78309
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    Electrical torques on the electrostatic gyro in the gyro relativity experiment (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A comprehensive discussion and calculation of electrical torques on an electrostatic gyro as they relate to the gyroscope experiment to test general relativity is presented. Drift rates were computed for some typical state of the art rotors, including higher harmonics in the rotor shape. The effect of orbital averaging of gravity gradient forces, roll averaging of torques, and the effect of spin averaging on the effective shape of the rotor were considered. The electrical torques are reduced sufficiently in a low g environment to permit a measurement of the relativistic drifts predicted by general relativity.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-78311
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    Distance corrections for single- and dual-color lasers by ray tracing (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The physical arc length difference between the red and blue beam of a dual-color laser generates an error term in determining Delta-n as well as n (the refractive index) and D (the line length). Numerical ray trace examples and theoretical approximations show that the resulting relative error Delta-D/D increases as D-squared. Error reduction by a factor of nearly 10 is possible by using the pressure, temperature, and humidity of both endpoints to calculate n. The present study results from a desire to improve the precision of monitoring the local and regional position of the Lunar Laser Ranging Observatory atop Haleakala, Maui, Hawaii; the monitoring of the earth's crustal deformation and strain is a primary concern of the study.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Geophysical Research; 85; Nov. 10
    Format: text
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  • 99
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    Thrust and ignition transients of the Space Shuttle solid rocket motor (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Techniques developed for predicting and analyzing ignition, pressurization, and thrust transients in large segmented motors were applied to the four developmental Space Shuttle solid rocket motors. Following the first test, attention was focused on understanding dynamic thrust and the rate of thrust increase during pressurization and predicting effects of reduced igniter mass flow rate and gas temperature. The close coupling between the igniter and the head-end segment and the high length-to-diameter ratio make understanding of the longitudinal pressure waves essential. The igniter performance along with igniter to head-end segment geometry govern the induction interval and head-end segment ignition. Following ignition of the head-end segment, subsequent flame spreading and pressurization tend to be motor properties which are not appreciably altered by changes in the head-end igniter mass flow rate.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-1137
    Format: text
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  • 100
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    Energy-selective SESD imaging utilizing a CMA (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A particularly simple conversion of a scanning Auger system for ESD ion energy distributions and scanning ESD has been developed. This approach combines the advantages of the small spot-size electron guns and mapping systems developed for SAM with the capability of ESD for the detection of hydrogen. Our intended use for the device is detection and mapping of surface concentrations of hydrogen on metals. The characteristics of SESD are illustrated with the preliminary results of an investigation into the ESD properties of hydrogenic adsorbates on Nb. It is shown that the ESDIED exhibit distinct differences indicative of the surface preparation, and that the ESD ion angular distributions have an effect on the observed contrast relationships in SESD.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Vacuum Science and Technology; 17; Nov
    Format: text
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