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  • SPACECRAFT PROPULSION AND POWER  (20)
  • Organic Chemistry
  • 1995-1999  (2)
  • 1980-1984  (26)
  • 1
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    Results of tests of MTA-2 TPS on the SRB hold-down bolt blast container (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The four solid rocket booster (SRB) hold-down posts are fastened to the mobile launch platform (MLP) with four large nuts. At liftoff the nuts are split with explosive changes to release the SRB/Shuttle. A blast container is placed over the nuts to protect the vehicle from flying debris. The blast container is a reusable part and has to be protected from aerodynamic heating during flight. The thermal protection system (TPS) used to protect these blast containers is cork. Fitting the flat cork sheet to this hemispherical shaped blast container is both time consuming and expensive. Another problem is removing the charred cork and epoxy glue from the blast containers. Replacements of this cork with another TPS material such as MTA-2 was examined. Heating rates along the centerline of the forward facing areas of the blast container were determined. The feasibility of using 1/2 in. MTA-2 on the SRB blast containers for protection from ascent, plume impingement and reentry heating is demonstrated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170891 , NAS 1.26:170891 , LMSC-HREC-TN-D867571
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Results of tests of the SRB aft skirt heat shield curtain in the MSFC Hot Gas Facility (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: During the first two space shuttle flights the aft skirt heat shield curtain performed well during ascent but failed during reentry. This exposed the inside of the skirt and its subsystems to reentry heating. The resulting exposure damaged various expensive systems items and therefore a curtain reassessment is required. As a part of this reassessment, tests were conducted in the MSFC Hot Gas Facility (HGF). The purposes of these tests were to determine if the curtain would fail in a manner similar to that in flight and to demonstrate that meaningful tests of the curtain can be conducted in the HGF.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170888 , NAS 1.26:170888 , LMSC-HREC-TM-D784643
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    High voltage distribution and grounding in high power spacecraft (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Many space missions proposed for the time period from 1985 to 2000 will require large spacecraft to support the onboard loads. In some cases, large electrical power systems will be needed to supply the electrical/electronic equipment loads. These electronic systems will be used for communications, radar, and experimental equipment for aid to earth's overcrowded communication systems, exploration of new energy resources, space exploration, and eventually to supplement terrestrial electric power utilities. For the near term (1985-1990), some of these systems have power levels to 50 kW. The long-term programs, 1990 to post-2000, could possibly have demands in the order of multimegawatts. The problems which have to be solved to construct the required high-voltage power supply systems are considered. Data and conceptual designs generated are found to indicate that grounding and bonding for high power systems can be accomplished in spacecraft by using either manual or automatic joining of the structural members.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    High voltage requirements and issues for the 1990's (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The development of high-power high-voltage space systems will require advances in power generation and processing. The systems must be reliable, adaptable, and durable for space mission success. The issues, which must be resolved in order to produce a high power system, are weight and volume reduction of components and modules and the creation of a reliable high repetition pulse power processor. Capacitor energy density must be increased by twice the present capacity and packaging must be reduced by a factor of 10 to 20 times. The packaging must also protect the system from interaction with the natural space environment and the induced environment, produced from spacecraft systems and environment interaction.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''84: Advanced energy systems - Their role in our future; Aug 19, 1984 - Aug 24, 1984; San Francisco, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    High voltage cabling for high power spacecraft (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Studies by NASA have shown that many of the space missions proposed for the time period 1980 to 2000 will require large spacecraft structures to be assembled in orbit. Large antennas and power systems up to 2.5 MW size are predicted to supply the electrical/electronic subsystems, solar electric subsystems, solar electric propulsion, and space processing for the near-term programs. Platforms of 100 meters/length for stable foundations, utility stations, and supports for these multi-antenna and electronic powered mechanisms are also being considered. This paper includes the findings of an analytic and conceptual design study for large spacecraft power distribution, and electrical loads and their influence on the cable and connector requirements for these proposed large spacecraft.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: In: NAECON 1981; May 19, 1981 - May 21, 1981; Dayton, OH
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Multi-hundred kW solar arrays for space (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A system-level approach has been applied in designing a cost-effective 300-1000 kW solar array for Low Earth Orbit (LEO) application with a mission time frame of mid-1980's. Technology investigations and performance and cost prognoses in the area of solar cells and reflector material form a key influence on array design and performance. Major tradeoffs were conducted between planar and concentrator concepts and between silicon and GaAs solar cells. Three baseline design concepts emerged: planar, low-CR concentrator (CR = 5), and high-CR concentrator (CR = 125). Combinations of these concepts with silicon and GaAs solar cells were analyzed in terms of electrical performance, thermal behavior, structural configuration, weight, stowed and deployed volume, and installation/deployment method. To identify the most cost-effective designs, a cost analysis of the candidate arrays was performed. The low-CR/GaAs array and the planar/silicon array demonstrate the greatest cost-effectiveness of the candidate arrays in terms of dollars/watt and energy life-cycle cost. Due to the high uncertainty of GaAs cell-cost prognoses, the sensitivity of the results to the GaAs cell cost is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Energy to the 21st century; Aug 18, 1980 - Aug 22, 1980; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
    Electronic Resource
    Electronic Resource
    Water Relaxation Measurements on Semiquinones of Various Flavoproteins (1982)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 65 (1982), S. 2422-2430 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: The water relaxation rates of several flavoproteins in the semiquinone state have been investigated by the spin echo technique. The results indicate a rather unspecific interaction between water and the protein-bound flavosemiquinones. An average interaction distance of 0.3-0.5 nm has been estimated. From the temperature dependence of the rate constants the free energy of activation for proton exchange is calculated to be about 17 kJ/mol. The rate of proton exchange is around 1011 s-1 for the flavosemiquinones investigated are accessible to water regardless of their ionic state.The large difference in relaxation rates of water protons between D- and L- amino-acid oxidases is noticeable. Oxynitrilase exhibits the highest whereas Azotobacter vinelandii flavodoxin shows the lowest water relaxation rate of the flavoproteins studied. The results are discussed in relation to the visible-light absorption properties of the flavoproteins.
    Additional Material: 1 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19820650807
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    Paper (German National Licenses)
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  • 9
    Electronic Resource
    Electronic Resource
    Laser-Induced Luminescence of Flavinium Salts (1980)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 63 (1980), S. 1296-1303 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Flavinium salts dissolved in an ethanolic glass exhibit blue fluorescence and orange-red phosphorescence upon excitation with a UV. line from an argon ion laser equipped with UV. optics. This arrangement enables the wavelength distribution and the time-dependence of the phosphorescence to be measured in a relatively short time. Four cationic flavins were investigated. In spite of the small difference in the chemical structure of the compounds studied, large differences in the spectral shapes and in the ratio of quantum efficiencies of phosphorescence and fluorescence became apparent. The phosphorescence lifetimes were of the same order of magnitude, which indicated a similar rate of depletion of the lowest excited triplet state for all four cations. However, the efficiency of triplet formation (intersystem crossing) is affected by slight structural modifications in the pyrimidine subnucleus of the flavinium salt. The results point to a possible role of vibronic spin-orbit coupling in the intersystem crossing.
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19800630521
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    Paper (German National Licenses)
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  • 10
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    Study of auxiliary propulsion requirements for large space systems, volume 2 (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A range of single shuttle launched large space systems were identified and characterized including a NASTRAN and loading dynamics analysis. The disturbance environment, characterization of thrust level and APS mass requirements, and a study of APS/LSS interactions were analyzed. State-of-the-art capabilities for chemical and ion propulsion were compared with the generated propulsion requirements to assess the state-of-the-art limitations and benefits of enhancing current technology.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168193-VOL-2 , NAS 1.26:168193-VOL-2 , D180-27728-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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