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  • LUNAR AND PLANETARY EXPLORATION  (405)
  • ASTROPHYSICS  (177)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE
  • Life and Medical Sciences
  • Lunar and Planetary Science and Exploration
  • MATERIALS, METALLIC
  • 2005-2009
  • 1975-1979  (567)
  • 1970-1974  (191)
  • 1950-1954
  • 1925-1929  (2)
  • 2010
  • 1978  (285)
  • 1975  (282)
  • 1974  (191)
  • 1925  (2)
Collection
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  • 2005-2009
  • 1975-1979  (567)
  • 1970-1974  (191)
  • 1950-1954
  • 1925-1929  (2)
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Year
  • 1
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    The imaging photopolarimeter experiment on Pioneer 11 (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: For 2 weeks continuous imaging, photometry, and polarimetry observations were made of Jupiter and the Galilean satellites in red and blue light from Pioneer 11. Measurements of Jupiter's north and south polar regions were possible because the spacecraft trajectory was highly inclined to the planet's equatorial plane. One of the highest resolution images obtained is presented here along with a comparison of a sample of our photometric and polarimetric data with a simple model. The data seem consistent with increased molecular scattering at high latitudes.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Science; 188; May 2
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Temperature emission spectrum of exoelectrons of lunar regolith (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Thermostimulated exoelectronic emission of eight fragments of regolith returned by the Soviet Luna 16 automatic station was studied. The nature of the exoemission glove-curves was determined by particle type. Fragments of breccia, sinter, slag, anorthosite, glass plate, and leucocratic gabbro after the first heating disclosed a single exoemission maximum, whose temperature position is in the range 115 to 200 C. The data obtained indicate the complex and inhomogeneous energy structure of some regolith fragments. The presence of surface states capable of forming sorptive bonds can be assumed for most particles. The exoemission of anorthosite, olivine, and the glass spherule is due to the presence of formation defects at their surfaces.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 528-537
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    NASA TECHNICAL REPORTS
  • 3
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    Exoelectronic emission of particles of lunar surface material (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A secondary electron multiplier was used to study the thermostimulated exoelectronic emission of particles of lunar surface material returned by the Soviet Luna 16 automatic station. The natural exoemission from fragments of slag, glass, anorthosite, and a metallic particle was recorded in the isochronic and isothermal thermostimulation regimes. The temperature of emission onset depended on the type of regolith fragment. For the first three particles the isothermal drop in emission is described by first-order kinetic equations. For the anorthosite fragment, exoemission at constant temperature is characterized by a symmetric curve with a maximum. These data indicate the presence of active surface defects, whose nature can be due to the prehistory of the particles.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 521-527
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    NASA TECHNICAL REPORTS
  • 4
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    Some results of track method of investigating Luna 16 lunar material (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Preliminary data from an investigation of tracks in olivine crystals, separated from the five zones of a lunar surface material core, are reported. The gradients of track densities, their lengths, and their angular distribution were measured with an optical microscope. Throughout the core depth (35 cm) crystals bearing traces of exposure to low energy solar cosmic rays were found, indicating the occurrence of mixing processes in the surficial layer of lunar surface material. The age of the occurrence of the samples investigated on the lunar surface, calculated from the track density, is in the interval 0.7 to 16 million years.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 379-387
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    NASA TECHNICAL REPORTS
  • 5
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    Mars sample return through parking orbit (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A Mars surface sample return mission using Mars direct entry and Mars parking orbit return is described. The mission is designed for a minimum energy requirement and is relatively simple in comparison to the alternative Mars orbital rendezvous mode. The design calls for minimal science, and uses a single Titan IIIE/Centaur launch vehicle. The primary science areas included are biology, biochemistry, geochemistry, and petrology, for detecting life, age dating, and determining chemical compositions and rock types. The total minimum sample requirement would be 30 g. Sampling conditions and recommended measurements are discussed. Maximum use of hardware and experience from the Mariner, Pioneer, and Viking missions is contemplated. The profile for a 1979 conjunction-class mission would include a total time of 1025 days, including one year in Mars parking orbit after sampling. The lander structure, components, and recovery alternatives are explained.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Astronautics and Aeronautics; 13; Jan. 197
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    NASA TECHNICAL REPORTS
  • 6
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    Preliminary study of propulsion systems and airplane wing parameters for a US Navy subsonic V/STOL aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two V/STOL propulsion concepts were evaluated in a common aircraft configuration. One propulsion system consists of cross coupled turboshaft engines driving variable pitch fans. The other system is a gas coupled combination of turbojet gas generators and tip turbine fixed pitch fans. Evaluations were made of endurance at low altitude, low speed loiter with equal takeoff fuel loads. Effects of propulsion system sizing, bypass ratio, and aircraft wing planform parameters were investigated and compared. Shaft driven propulsion systems appear to result in better overall performance, although at higher installed weight, than gas systems.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-73652 , E-9519
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Mineralogy, petrology, and chemistry of basalt fragments returned by Luna 16 (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Mineralogical, petrological, and chemical analyses, along with Rb-Sr age and Ar-40/Ar-39 measurements, were carried out with the B-1 sample returned from the Luna 16 mission. The sample, weighing 62 mg, is a fine-grain basalt of ophitic structure. It differs from the Apollo samples in that the pyroxene and plagioclass contents are almost identical, and the ilmenite content (7%) lies between those of the Apollo-11 and Apollo-12 samples. Chemically, it is characterized by a high Sr content and a high K/U ratio.
    Keywords: LUNAR AND PLANETARY EXPLORATION
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    NASA TECHNICAL REPORTS
  • 8
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    Full-scale upper-surface-blown flap noise (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A highly noise-suppressed TF 34 engine was used to investigate the noise of several powered lift configurations involving upper-surface-blown (USB) flaps. The configuration variables were nozzle type (i.e. slot and circular with deflector), flap chord-length, and flap angle. The results of velocity surveys at both the nozzle exit and the flap trailing edge are used for correlation of the noise data. Configurations using a long flap design were 4 dB quieter than a short flap typical of current trends in USB flap design. The lower noise for the long flap is attributed primarily to the greater velocity decay of the jet at the flap trailing edge. The full-scale data revealed substantially more quadrupole noise in the region near the deflected jet than observed in previous sub-scale tests.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 750609 , Society of Automotive Engineers, Air Transportation Meeting; May 06, 1975 - May 08, 1975; Hartford, CT
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    NASA TECHNICAL REPORTS
  • 9
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    Volatile and siderophilic trace elements in the soils and rocks of Taurus-Littrow (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Data are reported on 22 elements determined on 11 soils, one soil breccia, and two crystalline rocks from the Apollo 17 Taurus-Littrow landing site. The elements determined include the siderophilic elements Ni, Ge, Ir, and Au. The volatile elements considered include Na, Zn, Cd, and In. Attention is given to the extralunar component in soils and breccias, the orange-glass component in soils and breccias, and the labile elements in lunar soils.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Science Conference; Mar 18, 1974 - Mar 22, 1974; Houston, TX
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    NASA TECHNICAL REPORTS
  • 10
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    Martian atmosphere modeling between 0.4 and 3.5 microns - Comparison of theory and experiment (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A model of the lower atmosphere of Mars has been constructed that combines aerosol absorption and scattering with a line-by-line analysis of CO2 and H2O in a multilayer radiative transfer program. Aerosol composition previously inferred from the NASA Lear Jet Observatory data was used to measure the optical complex indices of refraction of appropriate Martian analogs from 0.4 to 2.5 microns. The aerosol vertical particle density scale was deduced using the Viking camera observations of the soil and sky intensities between 0.4 and 1.0 microns in comparison with those modeled using a multilayer Mie scattering program. A comparison of observed Mars atmospheric absorptions was made with those obtained using Lorentz, Voigt, and Doppler line profiles in a multilayer model of the CO2 and H2O. The Voigt line profile of CO2 absorption at approximately 4976 kaysers was then combined in a multilayer aerosol model of the Martian atmosphere. An evaluation of the effect on the line shape was made using several aerosol loadings.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: In: Symposium on Planetary Atmospheres; Aug 16, 1977 - Aug 19, 1977; Ottawa; Canada
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