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  • ASTROPHYSICS  (41)
  • SPACE VEHICLES  (41)
  • CHEMISTRY
  • PROPULSION SYSTEMS
  • 1985-1989
  • 1970-1974  (141)
  • 1965-1969
  • 1974  (141)
Collection
Keywords
Years
  • 1985-1989
  • 1970-1974  (141)
  • 1965-1969
Year
  • 1
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    An investigation of the cosmic radiation in the vicinity of the moon on the Luna 10, 11, and 12 artificial lunar satellites (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Research on the primary cosmic radiation and solar cosmic rays from the Luna 10, 11, and 12 artificial lunar satellites is reviewed. Data on the vertical distribution of cosmic rays above the moon's surface are presented, and the albedo for the primary radiation is determined. The fluxes of electrons with energies from 30 to 300 keV were registered in the solar cosmic rays. Rapid variations of the electron flux were observed. The angular distributions of 0.5-10 MeV protons moving together with the corpuscular streams responsible for Forbush decreases were investigated.
    Keywords: ASTROPHYSICS
    Type: Interplanet. Medium and Phys. of the Magnetosphere (NASA-TT-F-784); p 151-173
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Estimates of the Venus atmosphere optical characteristics with application to the problem of photographing its clouds and surface (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Optical parameters investigated and solved for included: (1) cloud layer albedo and cloud cover optical thickness; (2) planetary surface self-radiation influence; (3) light flux distribution as function of atmospheric height; (4) upper estimate of the observed contrasts; (5) surface optical parameters; and (6) contrast decrease with altitude.
    Keywords: ASTROPHYSICS
    Type: Space Iconics (NASA-TT-F-798); p 121-135
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Applicability of the diffusion approximation (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Several methods using an approximate form of the scattering indicatrix are discussed for simplifying the calculation of radiation transport in planetary atmospheres.
    Keywords: ASTROPHYSICS
    Type: Space Iconics (NASA-TT-F-798); p 75-84
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Three-dimensional tertiary structure of yeast phenylalanine transfer RNA (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Results of an analysis and interpretation of a 3-A electron density map of yeast phenylalanine transfer RNA. Some earlier detailed assignments of nucleotide residues to electron density peaks are found to be in error, even though the overall tracing of the backbone conformation of yeast phenylalanine transfer RNA was generally correct. A new, more comprehensive interpretation is made which makes it possible to define the tertiary interactions in the molecule. The new interpretation makes it possible to visualize a number of tertiary interactions which not only explain the structural role of most of the bases which are constant in transfer RNAs, but also makes it possible to understand in a direct and simple fashion the chemical modification data on transfer RNA. In addition, this pattern of tertiary interactions provides a basis for understanding the general three-dimensional folding of all transfer RNA molecules.
    Keywords: CHEMISTRY
    Type: Science; 185; Aug. 2
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Extended temperature range ACPS thruster investigation (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The successful hot fire demonstration of a pulsing liquid hydrogen/liquid oxygen and gaseous hydrogen/liquid oxygen attitude control propulsion system thruster is described. The test was the result of research to develop a simple, lightweight, and high performance reaction control system without the traditional requirements for extensive periods of engine thermal conditioning, or the use of complex equipment to convert both liquid propellants to gas prior to delivery to the engine. Significant departures from conventional injector design practice were employed to achieve an operable design. The work discussed includes thermal and injector manifold priming analyses, subscale injector chilldown tests, and 168 full scale and 550 N (1250 lbF) rocket engine tests. Ignition experiments, at propellant temperatures ranging from cryogenic to ambient, led to the generation of a universal spark ignition system which can reliably ignite an engine when supplied with liquid, two phase, or gaseous propellants. Electrical power requirements for spark igniter are very low.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-134655
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Compatibility testing of spacecraft materials and space-storable liquid propellants (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Compatibility measurements were made for aluminum 2219-T87 alloy and titanium 6Al-4V alloy in the presence of liquid fluorine and flox. Results of post test characterization after exposure durations of 61 and 70 weeks are presented. Results of the total test program are analyzed.
    Keywords: CHEMISTRY
    Type: NASA-CR-139281 , TRW-23162-6023-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Effect of gaseous and solid simulated jet plumes on an 040A space shuttle launch configuration at m=1.6 to 2.2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of plume-induced flow separation and aspiration effects due to operation of both orbiter and the solid rocket motors on a 0.019-scale model of the launch configuration of the Space Shuttle Vehicle is determined. Longitudinal and lateral-directional stability data were obtained at Mach numbers of 1.6, 2.0, and 2.2 with and without the engines operating. The plumes exiting from the engines were simulated by a cold-gas jet supplied by an auxiliary 200-atm air supply system and solid-body plume simulators. The aerodynamic effects produced by these two simulation procedures are compared. The parameters most significantly affected by the jet plumes are pitching moment, elevon control effectiveness, axial force, and orbiter wing loads. The solid rocket motor (SRM) plumes have the largest effect on the aerodynamic characteristics. The effect of the orbiter plumes in combination with the SRM plumes is also significant. Variations in the nozzle design parameters and configuration changes can reduce the jet plume-induced aerodynamic effects.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-3032 , A-5212
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Investigation of noise from full-scale high bypass engine and blown flap system (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A summary is presented of an acoustic test program for investigating engine noise suppression and jet/flap interaction noise associated with an EBF STOL powered lift system. A highly suppressed TF-34 engine and EBF wing were used in the investigation. The engine was suppressed 21 PndB to a level of 94 PndB. An UTW powered lift system was tested with conventional, mixer, and decayer-type nozzles. The configuration with velocity decayer nozzle and acoustically treated shroud had the lowest noise (98 PndB). An OTW configuration with non-decayer nozzle was about 10 db quieter than the corresponding UTW system. UTW and OTW noise data are compared with scale model correlations.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71539 , E-7946 , Air Transport Meeting; Apr 30, 1974 - May 02, 1974; Dallas
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Foreign inclusions in stony meteorites. II - Rare gases and oxygen isotopes in a carbonaceous chondritic xenolith in the Plainview gas-rich chondrite (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Foreign inclusions in stony meteorites. II - Rare gases and oxygen isotopes in a carbonaceous chondritic xenolith in the Plainview gas-rich chondrite
    Keywords: CHEMISTRY
    Type: Geochimica et Cosmochimica Acta; 38; June 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Sealing technology for aircraft gas turbine engines (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Experimental evaluation under simulated engine conditions revealed that conventional mainshaft seals have disadvantages of high gas leakage rates and wear. An advanced seal concept, the self-acting face seal, has a much lower gas leakage rate and greater pressure and speed capability. In endurance tests (150 hr) to 43 200 rpm the self-acting seal wear was not measurable, indicating noncontact sealing operation was maintained even at this high rotative speed. A review of published data revealed that the leakage through gas path seals has a significant effect on TSFC, stall margin and engine maintenance. Reducing leakages by reducing seal clearances results in rubbing contact, and then the seal thermal response and wear determines the final seal clearances. The control of clearances requires a material with the proper combination of rub tolerance (abradability) and erosion resistance. Increased rub tolerance is usually gained at the expense of reduced erosion resistance and vice versa.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-71607 , E-8096 , Propulsion Conf.; Oct 21, 1974 - Oct 24, 1974; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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