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  • Weitere Quellen  (21)
  • Spacecraft Propulsion and Power  (20)
  • 551  (1)
  • Magnetism
  • Superfluidity and superconductivity
  • Organic Chemistry
  • 1
    Publikationsdatum: 2021-03-29
    Beschreibung: Molten I-type cosmic spherules formed by heating, oxidation and melting of extraterrestrial Fe,Ni metal alloys. The entire oxygen in these spherules sources from the atmosphere. Therefore, I-type cosmic spherules are suitable tracers for the isotopic composition of the upper atmosphere at altitudes between 80 and 115 km. Here we present data on I-type cosmic spherules collected in Antarctica. Their composition is compared with the composition of tropospheric O2. Our data suggest that the Earth's atmospheric O2 is isotopically homogenous up to the thermosphere. This makes fossil I-type micrometeorites ideal proxies for ancient atmospheric CO2 levels.
    Beschreibung: Open-Access-Publikationsfonds 2017
    Schlagwort(e): oxygen isotope; upper Earth’s atmosphere; cosmic spherules ; 551
    Sprache: Englisch , Englisch
    Materialart: article , publishedVersion
    Standort Signatur Erwartet Verfügbarkeit
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  • 2
    Publikationsdatum: 2018-06-08
    Beschreibung: 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.
    Schlagwort(e): Spacecraft Propulsion and Power
    Materialart: 2003 Joint Propulsion Conference; Huntsville, AL; United States
    Format: text
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  • 3
    Publikationsdatum: 2018-06-12
    Beschreibung: Nuclear and radioisotope powered electric thrusters are being developed as primary in-space propulsion systems for potential future robotic and piloted space missions. Possible applications for high power nuclear electric propulsion include orbit raising and maneuvering of large space platforms, lunar and Mars cargo transport, asteroid rendezvous and sample return, and robotic and piloted planetary missions, while lower power radioisotope electric propulsion could significantly enhance or enable some future robotic deep space science missions. This paper provides an overview of recent U.S. high power electric thruster research programs, describing the operating principles, challenges, and status of each technology. Mission analysis is presented that compares the benefits and performance of each thruster type for high priority NASA missions. The status of space nuclear power systems for high power electric propulsion is presented. The paper concludes with a discussion of power and thruster development strategies for future radioisotope electric propulsion systems,
    Schlagwort(e): Spacecraft Propulsion and Power
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 4
    Publikationsdatum: 2018-06-08
    Beschreibung: A long duration test of the DSl flight spare ion thruster (FT2) is presently being conducted at the Jet Propulsion Laboratory. To, date the thruster has accumulated over 23,500 hours of operation, and 190 kg of Xenon propellant, over 230% of the initial design life. The primary objectives of the test include the processing of 200 kg of Xenon propellant, the identification of unknown failure modes, the characterization and drivers of these failure modes, and to measure performance degradation as the thruster wears. The test is fitted with an extensive array of diagnostics to measure engine wear and performance degradation. To date the most notable erosion processes include severe discharge cathode keeper erosion, accelerator grid erosion, reduction in electrical isolation of the neutralizer assembly, and deposit formation within the neutralizer orifice, reducing margin from plume mode. Over the past 23,500 hours of operation, performance degradation has been minimal, and it is anticipated that the above erosion processes will not preclude the thruster from processing over 200 kg of Xenon.
    Schlagwort(e): Spacecraft Propulsion and Power
    Materialart: AIAA/ASME/SAE/ASEE 38th Joint Propulsion Conference and Exhibit; Indianapolis, IN; United States
    Format: text
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  • 5
    Publikationsdatum: 2018-06-08
    Schlagwort(e): Spacecraft Propulsion and Power
    Materialart: Advanced Space Propulsion Workshop; Pasadena, CA; United States
    Format: text
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  • 6
    Publikationsdatum: 2018-06-08
    Schlagwort(e): Spacecraft Propulsion and Power
    Materialart: 28th International Electric Propulsion Conference; Toulouse; France
    Format: text
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  • 7
    Publikationsdatum: 2018-06-08
    Schlagwort(e): Spacecraft Propulsion and Power
    Materialart: 28th International Electric Propulsion Conference; Toulouse; France
    Format: text
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  • 8
    Publikationsdatum: 2019-07-13
    Beschreibung: The Deep Space 1 (DSl) spare flight thruster (FT2) was operated for 30,352 hours during the extended life test (ELT). The test was performed to validate the service life of the thruster, study known and identify unknown life limiting modes. Several of the known life limiting modes involve the ion optics system. These include loss of structural integrity for either the screen grid or accelerator grid due to sputter erosion from energetic ions striking the grid, sputter erosion enlargement of the accelerator grid apertures to the point where the accelerator grid power supply can no longer prevent electron backstreaming, unclearable shorting between the grids causes by flakes of sputtered material, and rouge hole formation due to flakes of material defocusing the ion beam. Grid gap decrease, which increases the probability of electron backstreaming and of arcing between the grids, was identified as an additional life limiting mechanism after the test. A combination of accelerator grid aperture enlargement and grid gap decrease resulted in the inability to prevent electron backstreaming at full power at 26,000 hours of the ELT. Through pits had eroded through the accelerator grid webbing and grooves had penetrated through 45% of the grid thickness in the center of the grid. The upstream surface of the screen grid eroded in a chamfered pattern around the holes in the central portion of the grid. Sputter deposited material, from the accelerator grid, adhered to the downstream surface of the screen grid and did not spall to form flakes. Although a small amount of sputter deposited material protruded into the screen grid apertures, no rouge holes were found after the ELT.
    Schlagwort(e): Spacecraft Propulsion and Power
    Materialart: AIAA Paper 2004-3610 , 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 11, 2004 - Jul 14, 2004; Fort Lauderdale, FL; United States
    Format: text
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  • 9
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    Unbekannt
    In:  Other Sources
    Publikationsdatum: 2019-08-26
    Beschreibung: During the Extended Life Test of the DS1 flight spare ion thruster, the engine was subjected to sensitvity testing in order to characterize the macroscopic dependence of discharge chamber sensitivity to a +\-3% vatiation in main flow, cathode flow and beam current, and to +\5% variation in beam and accelerator voltage, was determined for the minimum- (THO), half- (TH8) and full power (TH15) throttle levels. For each power level investigared, 16 high/low operating conditions were chosen to vary the flows, beam current, and grid voltages in in a matrix that mapped out the entire parameter space. The matrix of data generated was used to determine the partial derivative or senitivity of the dependent parameters--discharge voltage, discharge current, discharge loss, double-to-single-ion current ratio, and neutralizer-keeper voltage--to the variation in the independent parameters--main flow, cathode flow, beam current, and beam voltage. The sensititivities of each dependent parameter with respect to each independent parameter were determined using a least-square fit routine. Variation in these sensitivities with thruster runtime was recorded over the duration of the ELT, to detemine if discharge performance changed with thruster wear. Several key findings have been ascertained from the sensitivity testing. Discharge operation is most sensitve to changes in cathode flow and to a lesser degree main flow. The data also confirms that for the NSTAR configuration plasma production is limited by primary electron input due to the fixed neutral population. Key sensitivities along with their change with thruster wear (operating time) will be presented. In addition double ion content measurements with an ExB probe will also be presented to illustrate beam ion production and content sensitivity to the discharge chamber operating parameteres.
    Schlagwort(e): Spacecraft Propulsion and Power
    Materialart: IEPC-2007-010 , International Electric Propulsion Conference; Sep 17, 2007 - Sep 20, 2007; Florence; Italy
    Format: text
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  • 10
    Publikationsdatum: 2019-07-13
    Beschreibung: Interest in science objectives at the outer planets, specifically at the moons of Jupiter, has spurred the development of high-power electric propulsion systems under the Prometheus program.
    Schlagwort(e): Spacecraft Propulsion and Power
    Materialart: AIAA Paper 2005-4412 , 41st AIAA Joint Propulsion Conference; Jul 10, 2005 - Jul 13, 2005; Tuscon, AZ; United States
    Format: text
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