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  • SPACECRAFT PROPULSION AND POWER  (15)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (1)
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  • 1
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    Evaluation of charge control techniques on spacecraft thermal surfaces (electrostatic discharge study) (1980)
    In:  Other Sources
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    Publikationsdatum: 2016-06-07
    Beschreibung: The charging and discharging characteristics of various dielectric materials commonly used on spacecraft were tested. The experimental apparatus and the calculations used to analyze the data generated during the testing are described. The test technique, results, and analysis used are presented. Indium tin oxide coated Teflon, Kapton, and quartz do not charge significantly. CTL 15 white paint shows no large charge build up. Pinholes in Teflon and Kapton increase the leakage through the sample and reduce the energy released in an arc. Conductive grids in Teflon and Kapton reduce the arc energy by two orders of magnitude over untreated samples. Extreme low temperatures (-195 C) do not significantly increase the arc energy of the gridded sample.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 320-341
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Retrofit and verification test of a 30-cm ion thruster (1980)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Twenty modifications were found to be necessary and were approved by design review. These design modifications were incorporated in the thruster documents (drawings and procedures) to define the J series thruster. Sixteen of the design revisions were implemented in a 900 series thruster by retrofit modification. A standardized set of test procedures was formulated, and the retrofit J series thruster design was verified by test. Some difficulty was observed with the modification to the ion optics assembly, but the overall effect of the design modification satisfies the design objectives. The thruster was tested over a wide range of operating parameters to demonstrate its capabilities.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: NASA-CR-165233
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    Engineering Model 8-cm Thruster System (1978)
    In:  Other Sources
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    Publikationsdatum: 2019-07-13
    Beschreibung: Development of an Engineering Model 8-cm Mercury Ion Thruster System for Satellite Control has been successfully completed. This system operates at a specific impulse in excess of 2600 sec, produces a thrust of 5 mN with a total input power of 165 W; it has a dry mass of 16.6 kg and a mercury-propellant-reservoir capacity of 8.75 kg. This paper summarizes the development work, the system characteristics and performance, and the testing undertaken to verify the design.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 78-646 , International Electric Propulsion Conference; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    One-millipound mercury ion thruster (1975)
    In:  Other Sources
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    Publikationsdatum: 2019-07-13
    Beschreibung: A mercury ion thruster has been developed for efficient operation at the nominal 1-mlb thrust level with a specific impulse of about 3,000 sec and a total power consumption of about 120 W. At a beam voltage of 1,200 V and beam current of 72 mA, the discharge chamber operates with a propellant efficiency of 93.8% at an ion-generation energy of 276 eV/ion. The 8-cm diameter thruster advances proven component technology to assure the capability for thruster operation over an accumulated beam-on time in excess of 20,000 hours with a capability for 10,000 on-off duty cycles. Discharge chamber optimization has combined stable current-voltage characteristics with high performance efficiency by careful placement of the discharge cathode near the location of a magnetic-field zero just upstream of the thruster endplate.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 75-386 , American Institute of Aeronautics and Astronautics, Electric Propulsion Conference; Mar 19, 1975 - Mar 21, 1975; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Modularized ion thruster (1976)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A modularized ion thruster system was developed for space-propulsion applications. Separate discharge chamber modules (DCMs) were optimized for operation at the thrust levels of T = 0.5 mlb and T = 2 mlb to accommodate the extended thrust range. These optimizations included modifications in the discharge-chamber components and the incorporation of ion machined accelerators in the beam-extraction systems. Performance of the optimized modules are summarized.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: NASA-CR-134667
    Format: application/pdf
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  • 6
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    IAPS (8-cm) ion thruster cyclic endurance test (1984)
    In:  Other Sources
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    Publikationsdatum: 2019-07-13
    Beschreibung: Attention is given to the cyclic endurance qualification test, performed in a vacuum facility with a liquid nitrogen-cooled cryosurface and a frozen mercury target, to which a mercury-ion thruster representative of Ion Auxiliary Propulsion System (IAPS) thrusters was subjected. At the time that the endurance test was successfully concluded, upon consumption of the IAPS propellant tank's mercury, 8,471 hours of 'beam-on time' and 599 cycles had been accumulated. The system's Power Electronics Unit accumulated 10,268 hours of test time with high voltage applied to the operating thruster or dummy load.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: International Electric Propulsion Conference; May 28, 1984 - May 31, 1984; Tokyo; Japan
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 7
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    Ion thruster system (8-cm) cyclic endurance test (1984)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: This report describes the qualification test of an Engineering-Model 5-mN-thrust 8-cm-diameter mercury ion thruster which is representative of the Ion Auxiliary Propulsion System (IAPS) thrusters. Two of these thrusters are scheduled for future flight test. The cyclic endurance test described herein was a ground-based test performed in a vacuum facility with a liquid-nitrogen-cooled cryo-surface and a frozen mercury target. The Power Electronics Unit, Beam Shield, Gimal, and Propellant Tank that were used with the thruster in the endurance test are also similar to those of the IAPS. The IAPS thruster that will undergo the longest beam-on-time during the actual space test will be subjected to 7,055 hours of beam-on-time and 2,557 cycles during the flight test. The endurance test was successfully concluded when the mercury in the IAPS Propellant Tank was consumed. At that time, 8,471 hours of beam-on-time and 599 cycles had been accumulated. Subsequent post-test-evaluation operations were performed (without breaking vacuum) which extended the test values to 652 cycles and 9,489 hours of beam-on-time. The Power Electronic Unit (PEU) and thruster were in the same vacuum chamber throughout the test. The PEU accumulated 10,268 hr of test time with high voltage applied to the operating thruster or dummy load.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: NASA-CR-174745 , NAS 1.26:174745
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Characteristics of 30-centimeter mercury ion thrusters (1981)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The technology development of the 30-cm J-series mercury ion thruster for prime propulsion application in solar electric propulsion systems has been conducted at NASA-Lewis Research Center. This development included the fabrication and testing of the 30-cm thruster. The present J-series thruster design is the result of an intensive effort to eliminate real and potential design deficiencies that were uncovered during initial endurance, structural, and performance tests. A standardized set of test and data recording procedure was formulated to allow for the characterization of the J-series thruster. This paper briefly reviews the design of the J-series thruster and presents a compilation of recent test results that define the J-series thruster characteristics.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 81-0715 , International Electric Propulsion Conference; Apr 21, 1981 - Apr 23, 1981; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Status of the J-series 30-cm mercury ion thruster (1982)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper describes the status of the 30-cm J-series mercury ion thruster. This thruster was baselined for the Solar Electric Propulsion System (SEPS) vehicle. This thruster is described and several modifications plus suggested modifications are presented. Some of the modifications resulted from tests performed with the thruster. The operational characteristics of eight J-series thrusters are presented. Isolator contamination and flake formation are also discussed.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 82-1904 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Extended-performance 8-cm ion thruster operation (1982)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: The performance of an 8-cm ion thruster has been extended to 32-mN thrust, 4062-s specific impulse, and 0.033-mN/W thrust-to-power ratio. The design of this thruster is similar to the IAPS (Ion Auxiliary Propulsion System), which has a performance of 5-mN thrust, 3500-s specific impulse, and 0.036-mN/W thrust-to-power ratio. The above level of extended performance has been achieved by increasing the discharge power, ion-beam accelerating voltage, and propellant flowrate, and by modifying the propellant-vapor injection, discharge-chamber magnetic-field strength, high-voltage insulators, and electron baffle. This paper describes results obtained in characterizing the extended-performance operation of both the unmodified thruster (i.e., in an IAPS-like configuration) and the modified thruster. Lifetime-estimating measurements for the modified thruster at extended-performance conditions are also presented.
    Schlagwort(e): SPACECRAFT PROPULSION AND POWER
    Materialart: AIAA PAPER 82-1955 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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