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  • 1
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    Aqueous electrochemical intercalation of bromine into graphite fibers (2005)
    Elsevier
    Details
    Publication Date: 2005-01-01
    Print ISSN: 0008-6223
    Electronic ISSN: 1873-3891
    Topics: Chemistry and Pharmacology , Geosciences
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Conductive Composites Made Less Expensively (2005)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The use of electrically conductive composite structures for electrostatic dissipation, electromagnetic interference shielding, and ground return planes could save between 30 and 90 percent of the mass of the structure, in comparison to aluminum. One strategy that has been shown to make conducting composites effectively uses intercalated graphite fiber as the reinforcement. Intercalation--the insertion of guest atoms or molecules between the graphene planes--can lower the electrical resistivity of graphite fibers by as much as a factor of 10, without sacrificing mechanical or thermal properties.
    Keywords: Composite Materials
    Type: Research and Technology 2004
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Why the Moon? (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: In 2004, President George W. Bush proposed a new set of goals for NASA which have since been formalized by Congress as the revised United States Space Policy. A major goal is to return humans to the moon by 2020. This prompted a world-wide discussion about what our goals in space ought to be. In 2006 NASA surveyed potential stakeholders asking the question, "Why the Moon?" Responses were received from over 1000 entities including business, industry, academia, and 13 other space agencies. This presentation reports the responses to that questionnaire, as well as current plans for how the return to the moon will be accomplished.
    Keywords: Lunar and Planetary Science and Exploration
    Type: E-17341
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Synthesis, Decomposition and Characterization of Fe and Ni Sulfides and Fe and CO Nanoparticles for Aerospace Applications (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: We describe several related studies where simple iron, nickel, and cobalt complexes were prepared, decomposed, and characterized for aeronautics (Fischer-Tropsch catalysts) and space (high-fidelity lunar regolith simulant additives) applications. We describe the synthesis and decomposition of several new nickel dithiocarbamate complexes. Decomposition resulted in a somewhat complicated product mix with NiS predominating. The thermogravimetric analysis of fifteen tris(diorganodithiocarbamato)iron(III) has been investigated. Each undergoes substantial mass loss upon pyrolysis in a nitrogen atmosphere between 195 and 370 C, with major mass losses occurring between 279 and 324 C. Steric repulsion between organic substituents generally decreased the decomposition temperature. The product of the pyrolysis was not well defined, but usually consistent with being either FeS or Fe2S3 or a combination of these. Iron nanoparticles were grown in a silica matrix with a long-term goal of introducing native iron into a commercial lunar dust simulant in order to more closely simulate actual lunar regolith. This was also one goal of the iron and nickel sulfide studies. Finally, cobalt nanoparticle synthesis is being studied in order to develop alternatives to crude processing of cobalt salts with ceramic supports for Fischer-Tropsch synthesis.
    Keywords: Inorganic, Organic and Physical Chemistry
    Type: E-17335
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    NASA TECHNICAL REPORTS
  • 5
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    Extraction of Thermal Performance Values from Samples in the Lunar Dust Adhesion Bell Jar (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A simulation chamber has been developed to test the performance of thermal control surfaces under dusty lunar conditions. The lunar dust adhesion bell jar (LDAB) is a diffusion pumped vacuum chamber (10(exp -8) Torr) built to test material samples less than about 7 cm in diameter. The LDAB has the following lunar dust simulant processing capabilities: heating and cooling while stirring in order to degas and remove adsorbed water; RF air-plasma for activating the dust and for organic contaminant removal; RF H/He-plasma to simulate solar wind; dust sieving system for controlling particle sizes; and a controlled means of introducing the activated dust to the samples under study. The LDAB is also fitted with an in situ Xe arc lamp solar simulator, and a cold box that can reach 30 K. Samples of thermal control surfaces (2.5 cm diameter) are introduced into the chamber for calorimetric evaluation using thermocouple instrumentation. The object of this paper is to present a thermal model of the samples under test conditions and to outline the procedure to extract the absorptance, emittance, and thermal efficiency from the pristine and sub-monolayer dust covered samples.
    Keywords: Lunar and Planetary Science and Exploration
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    NASA TECHNICAL REPORTS
  • 6
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    The Effects of Lunar Dust on EVA Systems During the Apollo Missions (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Mission documents from the six Apollo missions that landed on the lunar surface have been studied in order to catalog the effects of lunar dust on Extra-Vehicular Activity (EVA) systems, primarily the Apollo surface space suit. It was found that the effects could be sorted into nine categories: vision obscuration, false instrument readings, dust coating and contamination, loss of traction, clogging of mechanisms, abrasion, thermal control problems, seal failures, and inhalation and irritation. Although simple dust mitigation measures were sufficient to mitigate some of the problems (i.e., loss of traction) it was found that these measures were ineffective to mitigate many of the more serious problems (i.e., clogging, abrasion, diminished heat rejection). The severity of the dust problems were consistently underestimated by ground tests, indicating a need to develop better simulation facilities and procedures.
    Keywords: Space Transportation and Safety
    Type: NASA/TM-2005-213610/REV1 , E-15071-1/REV1 , This printing, numbered as NASA/TM-2005-213610/REV1, April 2007, replaces the previous version, NASA/TM-2005-213610, March 2005, (20050160460)in its entirety.
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    NASA TECHNICAL REPORTS
  • 7
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    Effect of Architecture on the Resistivity of Carbon Fiber Polymer Composites (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The electrical resistivity of carbon fiber laminar composites can be tailored by weave direction, fiber composition, resin composition, applied pressure, and fiber fraction. Although the weave direction was only found to be important in the case of high aspect ratio composites, the other factors were found to influence the resistivity generally. Most intriguing, the resistivity of composites with lamina of different fiber compositions follows a parallel resistor model. This opens the door for higher performance, lower cost composites to be fabricated from these mixed fiber composites.
    Keywords: Composite Materials
    Type: E-15086 , Carbon 2005; Jul 03, 2005 - Jul 07, 2005; Gyeongju; Korea, Republic of
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    NASA TECHNICAL REPORTS
  • 8
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    The Need for High Fidelity Lunar Regolith Simulants (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The case is made for the need to have high fidelity lunar regolith simulants to verify the performance of structures, mechanisms, and processes to be used on the lunar surface. Minor constituents will in some cases have major consequences. Small amounts of sulfur in the regolith can poison catalysts, and metallic iron on the surface of nano-sized dust particles may cause a dramatic increase in its toxicity. So the definition of a high fidelity simulant is application-dependent. For example, in situ resource utilization will require high fidelity in chemistry, meaning careful attention to the minor components and phases; but some other applications, such as the abrasive effects on suit fabrics, might be relatively insensitive to minor component chemistry while abrasion of some metal components may be highly dependent on trace components. The lunar environment itself will change the surface chemistry of the simulant, so to have a high fidelity simulant it must be used in a high fidelity simulated environment to get an accurate simulation. Research must be conducted to determine how sensitive technologies will be to minor components and environmental factors before they can be dismissed as unimportant.
    Keywords: Lunar and Planetary Science and Exploration
    Type: NASA/TM-2008-215261 , E-16528 , Space Resources Roundtable IX; Oct 25, 2008 - Oct 27, 2008; Golden, CO; United States
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    NASA TECHNICAL REPORTS
  • 9
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    Lunar Simulation in the Lunar Dust Adhesion Bell Jar (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Lunar Dust Adhesion Bell Jar has been assembled at the NASA Glenn Research Center to provide a high fidelity lunar simulation facility to test the interactions of lunar dust and lunar dust simulant with candidate aerospace materials and coatings. It has a sophisticated design which enables it to treat dust in a way that will remove adsorbed gases and create a chemically reactive surface. It can simulate the vacuum, thermal, and radiation environments of the Moon, including proximate areas of illuminated heat and extremely cold shadow. It is expected to be a valuable tool in the development of dust repellant and cleaning technologies for lunar surface systems.
    Keywords: Lunar and Planetary Science and Exploration
    Type: NASA/TM-2007-214704 , AIAA Paper-2007-0963 , 45th Aerospace Sciences Meeting and Exhibit; Jan 08, 2007 - Jan 11, 2007; Reno, NV; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Lunar Dust on Heat Rejection System Surfaces: Problems and Prospects (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Heat rejection from power systems will be necessary for human and robotic activity on the lunar surface. Functional operation of such heat rejection systems is at risk of degradation as a consequence of dust accumulation. The Apollo astronauts encountered marked degradation of performance in heat rejection systems for the lunar roving vehicle, science packages, and other components. Although ground testing of dust mitigation concepts in support of the Apollo mission identified mitigation tools, the brush concept adopted by the Apollo astronauts proved essentially ineffective. A better understanding of the issues associated with the impact of lunar dust on the functional performance of heat rejection systems and its removal is needed as planning gets underway for human and robotic missions to the Moon. Renewed emphasis must also be placed on ground testing of pristine and dust-covered heat rejection system surfaces to quantify degradation and address mitigation concepts. This paper presents a review of the degradation in performance of heat rejection systems encountered on the lunar surface to-date, and will discuss current activities underway to evaluate the durability of candidate heat rejection system surfaces and current dust mitigation concepts.
    Keywords: Lunar and Planetary Science and Exploration
    Type: NASA/TM-2007-214814 , STAIF Paper number 26 , Space Technology and Applications International Forum; Feb 11, 2007 - Feb 15, 2007; Albuquerque, NM; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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