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  • Spacecraft Propulsion and Power  (240)
  • Chemistry
  • Inorganic Chemistry
  • 2000-2004  (241)
  • 2003  (241)
  • 1
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    Patent law. Natural substances and patentable inventions (2003)
    American Association for the Advancement of Science (AAAS)
    Details
    Publication Date: 2003-05-31
    Description: 〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Demaine, Linda J -- Fellmeth, Aaron X -- New York, N.Y. -- Science. 2003 May 30;300(5624):1375-6.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉RAND, Santa Monica, CA 90401, USA. demaine@rand.org〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/12775825" target="_blank"〉PubMed〈/a〉
    Keywords: Aluminum Oxide ; Chemical Phenomena ; Chemistry ; Natural Science Disciplines ; Patents as Topic/*legislation & jurisprudence ; Plant Extracts ; Plant Roots ; Titanium ; United States
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science (AAAS)
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    PAPER CURRENT
  • 2
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    Planetary Protection Considerations for JIMO (2003)
    In:  CASI
    Details
    Publication Date: 2004-10-30
    Description: Europa is the only body in the solar system besides Mars that is currently viewed as a body of significant interest relative to the process of chemical evolution and/or the origin of life or for which scientific opinion provides a significant chance of contamination which could jeopardize a future biological experiment. Thus, both NASA and COSPAR policy require that Europa be protected from biological contamination that could result from scientific exploration conducted by robotic spacecraft. In 2000, the Task Group on the Forward Contamination of Europa (Space Studies Board) published its report on Preventing the Forward Contamination of Europa recommending a limit of 10(exp -4) probability of contamination of Europa's ocean per mission (at any time in the future) by a single viable terrestrial microbe. While NASA guidelines do not yet explicitly reflect this new recommendation, it is likely that the SSB recommendation will be adopted by NASA planetary protection in the form of a sterility requirement or at least a stringent total microbial burden requirement. In our presentation, we will present an overview of the anticipated planetary protection requirements for both orbiters and landers destined for Europa and some of the challenges these requirements will present.
    Keywords: Spacecraft Propulsion and Power
    Type: Forum on Concepts and Approaches for Jupiter Icy Moons Orbiter; 40; LPI-Contrib-1163
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The status of ion propulsion development and implementation at JPL in 2003 (2003)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: The successful demonstration of ion propulsion on NASA's Deep Space 1 mission has stimulated substantial interest in the application of this technology to future solar system exploration missions.
    Keywords: Spacecraft Propulsion and Power
    Type: 2003 Joint Propulsion Conference; Huntsville, AL; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Performance characterization of the Vaporizing Liquid Micro Thruster (VLM) (2003)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: A Vaporizing Liquid Micro-Thruster (VLM) microfabricated thruster was tested on water propellant on a thrust stand and performance data obtained.
    Keywords: Spacecraft Propulsion and Power
    Type: International Electric Propulsion Conference 2003; Toulouse; France
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    NASA TECHNICAL REPORTS
  • 5
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    Applications of secondary propulsion systems for microspacecraft, drag-free, and precision formation flying missions (2003)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Keywords: Spacecraft Propulsion and Power
    Type: 28th International Electric Propulsion Conference; Toulouse; France
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Performance characterization of the Vaporizing Liquid Micro Thruster (VLM) (2003)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Keywords: Spacecraft Propulsion and Power
    Type: Informational Electric Propulsion Conference; Toulouse; France
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Toroidal Tank Development for Upper-stages (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The advantages, development, and fabrication of toroidal propellant tanks are profiled in this viewgraph presentation. Several images are included of independent research and development (IR&D) of toroidal propellant tanks at Marshall Space Flight Center (MSFC). Other images in the presentation give a brief overview of Thiokol conformal tank technology development. The presentation describes Thiokol's approach to continuous composite toroidal tank fabrication in detail. Images are shown of continuous and segmented toroidal tanks fabricated by Thiokol.
    Keywords: Spacecraft Propulsion and Power
    Type: 5th Conference on Aerospace Materials, Processes, and Environmental Technology; NASA/CP-2003-212931
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Electron Radiation Effects on Candidate Solar Sail Material (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Solar sailing is a unique form of propulsion where a spacecraft gains momentum from incident photons. Solar sails are not limited by reaction mass and provide continual acceleration, reduced only by the lifetime of the lightweight film in the space environment and the distance to the Sun. Once thought to be difficult or impossible, solar sailing has come out of science fiction and into the realm of possibility. Any spacecraft using this propulsion method would need to deploy a thin sail that could be as large as many kilometers in extent. The availability of strong, ultra lightweight, and radiation resistant materials will determine the future of solar sailing. The National Aeronautics and Space Administration's (NASA) Marshall Space Flight Center (MSFC) is concentrating research into the utilization of ultra lightweight materials for spacecraft propulsion. The Space Environmental Effects Team at MSFC is actively characterizing candidate solar sail material to evaluate the thermo-optical and mechanical properties after exposure to space environmental effects. This paper will describe the irradiation of candidate solar sail materials to energetic electrons, in vacuum, to determine the hardness of several candidate sail materials.
    Keywords: Spacecraft Propulsion and Power
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Evaluation of New Repair Methods for Seal Surface Defects on Reusable Solid Rocket Motor (RSRM) Hardware (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The focus of the evaluation was to develop a back-up method to cell plating for the improvement or repair of seal surface defects within D6-AC steel and 7075-T73 aluminum used in the RSRM program. Several techniques were investigated including thermal and non-thermal based techniques. Ideally the repair would maintain the inherent properties of the substrate without losing integrity at the repair site. The repaired sites were tested for adhesion, corrosion, hardness, microhardness, surface toughness, thermal stability, ability to withstand bending of the repair site, and the ability to endure a high-pressure water blast without compromising the repaired site. The repaired material could not change the inherent properties of the substrate throughout each of the test in order to remain a possible technique to repair the RSRM substrate materials. One repair method, Electro-Spark Alloying, passed all the testing and is considered a candidate for further evaluation.
    Keywords: Spacecraft Propulsion and Power
    Type: 5th Conference on Aerospace Materials, Processes, and Environmental Technology; NASA/CP-2003-212931
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Combustion Of Interacting Droplet Arrays In Microgravity (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: Theory and experiments involving single droplet combustion date back to 1953, with the first microgravity work appearing in 1956. The problem of a spherical droplet burning in an infinite, quiescent microgravity environment is a classical problem in combustion research with the classical solution appearing in nearly every textbook on combustion. The microgravity environment offered by ground-based facilities such as drop towers and space-based facilities is ideal for studying the problem experimentally. A recent review by Choi and Dryer shows significant advances in droplet combustion have been made by studying the problem experimentally in microgravity and comparing the results to one dimensional theoretical and numerical treatments of the problem. Studying small numbers of interacting droplets in a well-controlled geometry represents a logical step in extending single droplet investigations to more practical spray configurations. Studies of droplet interactions date back to Rex and co-workers, and were recently summarized by Annamalai and Ryan. All previous studies determined the change in the burning rate constant, k, or the flame characteristics as a result of interactions. There exists almost no information on how droplet interactions a effect extinction limits, and if the extinction limits change if the array is in the diffusive or the radiative extinction regime. Thus, this study examined experimentally the effect that droplet interactions have on the extinction process by investigating the simplest array configuration, a binary droplet array. The studies were both in normal gravity, reduced pressure ambients and microgravity facilities. The microgravity facilities were the 2.2 and 5.2 second drop towers at the NASA Glenn Research Center and the 10 second drop tower at the Japan Microgravity Center. The experimental apparatus and the data analysis techniques are discussed in detail elsewhere.
    Keywords: Spacecraft Propulsion and Power
    Type: Seventh International Workshop on Microgravity Combustion and Chemically Reacting Systems; 1-4; NASA/CP-2003-212376-REV1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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