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  • 1
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    Environment-induced electrostatic discharges as the cause of Voyager 1 power-on resets (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The Pioneer and Voyager spacecraft all experienced anomalous behavior during their encounters with Jupiter. In particular, the Voyager 1 spacecraft experienced 42 electrical circuitry designed to protect the on-board computer from power fluctuations. Given the diversity of instrumentation and frequency of the anomalies observed by Voyager 1 in the inner magnetosphere of Jupiter, this set of data is particularly well suited as a case study. Although the nature of the anomalies clearly indicates a spacecraft-charging origin, the Voyager low-energy plasma data apparently imply absolute surface potentials of only a few tens of volts. It is thus difficult to explain the anomalies in terms of surface charging. The anomalies are, however, shown to be consistent with the hypothesis of internal charging of spacecraft parts and components.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 23; 323-330
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Electromagnetic interference assessment of an ion drive electric propulsion system (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: An electric propulsion thrust system has the capability of providing a high specific impulse for long duration scientific missions in space. The EMI from the elements of an ion engine was characterized. The compatibility of ion drive electric propulsion systems with typical interplanetary spacecraft engineering was predicted.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 185-190
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Radiated and conducted EMI from a 30-cm ion thruster (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: In order to properly assess the interaction of a spacecraft with the EMI environment produced by an ion thruster, the EMI environment was characterized. Therefore, radiated and conducted emissions were measured from a 30-cm mercury ion thruster. The ion thruster beam current varied from zero to 2.0 amperes and the emissions were measured from 5 KHz to 200 MHz. Several different types of antennas were used to obtain the measurements. The various measurements that were made included: magnetic field due to neutralizer/beam current loop; radiated electric fields of thruster and plume; and conducted emissions on arc discharge, neutralizer keeper and magnetic baffle lines.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 167-183
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Spacecraft interface circuitry sensitivity analysis (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: Mariner 1964 spacecraft interface circuit sensitivity analysis
    Keywords: ELECTRONICS
    Type: PROC. OF THE SPACECRAFT ELECTROMAGNETIC INTERFERENCE WORKSHOP 15 DEC. 1968; P 171-184
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Comparing CRRES Internal Discharge Monitor results with ground tests and published guidelines (2001)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Type: 7th Spacecraft Charging Technology Conference; Noordwijk; Netherlands
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Comparing CRRES internal discharge monitor results with ground tests and published guidelines (2001)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: Various attempts have been made to reconcile data from the CRRES IDM space experiment, and other space experiments with ground test results, with modeling and with guidelines.
    Type: 7th Spacecraft Charging Technology Conference; Noordwijk; Netherlands
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Description and analysis of 890-MHz noise-measuring equipment (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Ranger spacecraft noise measuring equipment for subsystem interference with spacecraft receiver
    Keywords: COMMUNICATIONS
    Type: NASA-CR-74888 , JPL-TR-32-898
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Design guidelines for assessing and controlling spacecraft charging effects (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The need for uniform criteria, or guidelines, to be used in all phases of spacecraft design is discussed. Guidelines were developed for the control of absolute and differential charging of spacecraft surfaces by the lower energy space charged particle environment. Interior charging due to higher energy particles is not considered. A guide to good design practices for assessing and controlling charging effects is presented. Uniform design practices for all space vehicles are outlined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-2361 , E-2073 , NAS 1.60:2361
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Electrostatic charging characteristics of thermal control paints as function of temperature (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The charging characteristics of paints for various uses on spacecraft under electron bombardment were studied. It was found that there is not a strong temperature dependence of the charging characteristics between -155 C and +30 C; and there is a noticeable hystereis effect as the electron beam energy is varied. Furthermore, all of the paints tested exhibit large secondary yields at low (approx. 1 keV) bombarding electron energies; and surfaces can charge either positively or negatively depending on the conditions and the paint. It was concluded that paints are not simple, will require more detailed study, and will probably act differently in multiple energy electron tests.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 209-319
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Electromagnetic interference of power conditioners for solar electric propulsion (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Electrical, multikilowatt power conditioning (PC) equipment needed on board a spacecraft utilizing solar electric propulsion creates an electromagnetic environment that is potentially deterimental to the science, navigation, and radio communication hardware. Within the scope of the solar electric propulsion system technology program, three lightweight, 2.5-kW PCs were evaluated in terms of their electromagnetic characteristics. It was found that the levels of radiated and conducted interference exceeded the levels anticipated for a solar electric propulsion mission. These noise emissions, however, were the result of deficient interference design in these models, rather than a basic inability to control interference in this type of PC.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-133229 , JPL-TM-33-623
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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