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  • 1
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    Ion collection from a plasma by a pinhole (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Ion focusing by a biased pinhole is studied numerically. Laplace's equation is solved in 3-D for cylindrical symmetry on a constant grid to determine the potential field produced by a biased pinhole in a dielectric material. Focusing factors are studied for ions of uniform incident velocity with a 3-D Maxwellian distribution superimposed. Ion currents to the pinhole are found by particle tracking. The focusing factor of positive ions as a function of initial velocity, temperature, injection radius, and hole size is reported. For a typical Space Station Freedom environment (oxygen ions having a 4.5 eV ram energy, 0.1 eV temperature, and a -140 V biased pinhole), a focusing factor of 13.35 is found for a 1.5 mm radius pinhole.
    Keywords: PLASMA PHYSICS
    Type: NASA. Johnson Space Center, 5th Annual Workshop on Space Operations Applications and Research (SOAR 1991), Volume 2; p 694-702
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A charging study of the ACTS satellite using NASCAP (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The results of a charging study conducted with the NASA Charging Analyzer Program (NASCAP) using a model of the Advanced Communications Technology Satellite (ACTS) are presented. The electrostatic discharge mechanisms are described including the field and potential threshold values that were monitored during the NASCAP simulation. Particular attention is given to the charging behavior of the ACTS inclined antennas. The data obtained indicate that the possibility of a discharge occurring in the immediate vicinity of the antennas is minimal when the semiconducting paint layer on the antenna's front surface has sufficient surface conductivity. It is shown that the metallized multilayer insulating blanket ACTS design provides good electrostatic discharge control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 91-1471
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Ionospheric plasma flow about a system of electrically biased flat plates (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The steady state interaction of two electrically biased parallel plates immersed in a flowing plasma characteristic of low earth orbit is studied numerically. Fluid equations are developed to describe the motion of the cold positively charged plasma ions, and are solved using finite-differences in two dimensions on a Cartesian grid. The behavior of the plasma electrons is assumed to be described by the Maxwell-Boltzmann distribution. Results are compared to an analytical and a particle simulation technique for a simplified flow geometry consisting of a single semi-infinite negatively biased plate. Comparison of the extent of the electrical disturbance into the flowing plasma and the magnitude of the current collected by the plate is very good. The interaction of two equally biased parallel plates is studied as a function of applied potential. The separation distance at which the current collected by either plate decreases by five and twenty percent is determined as a function of applied potential. The percent decreases were based on a non-interacting case. The decrease in overall current is caused by a decrease in ionic density in the region between the plates. As the separation between the plates decreases, the plates collect the ions at a faster rate than they are supplied to the middle region by the oncoming plasma flow. The docking of spacecraft in orbit is simulated by moving two plates of unequal potential toward one another in a quasi-static manner. One plate is held at a large negative potential while the other floats electrically in the resulting potential field. It is found that the floating plate does not charge continuously negative as it approaches the other more negatively biased plate. Instead, it charges more and then less negative as ionic current decreases and then increases respectively upon approach. When the two plates come into contact, it is expected that the electrically floating plate will charge rapidly negative to a potential near that of the other plate.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-191119 , E-7732 , NAS 1.26:191119
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Operating in the space plasma environment: A spacecraft charging study of the Solar X-ray Imager (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This study presents the results of a spacecraft charging effects protection study conducted on the Solar X-ray Imager (SXI). The SXI is being developed by NASA Marshall Space Flight Center for NOAA's Space Environment Laboratory, and will be used to aid in forecasting energetic particle events and geomagnetic storms. Images will provide information on the intensity and location of solar flares, coronal mass ejections, and high speed solar streams. The SXI will be flown on a next-generation GOES sometime in the mid to late 1990's. Charging due to the encounter with a worst-case magnetic substorm environment is modeled using the NASCAP/GEO computer code. Charging levels of exterior surfaces and the floating potential of the spacecraft relative to plasma are determined as a function of spacecraft design, operational configuration, and orbital conditions. Areas where large surface voltage gradients exist on or near the SXI are identified as possible arc-discharge sites. Results of the charging analysis are then used to develop design recommendations that will limit the effects of spacecraft charging on the SXI operation.
    Keywords: PLASMA PHYSICS
    Type: NASA-TM-110644 , NAS 1.15:110644
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    TROPIX plasma interactions group report (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The purpose is to summarize the spacecraft charging analysis conducted by the plasma interactions group during the period from April 1993 to July 1993, on the proposed TROPIX spacecraft, and to make design recommendations which will limit the detrimental effects introduced by spacecraft charging. The recommendations were presented to the TROPIX study team at a Technical Review meeting held on 15 July 1993.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-191149 , E-8169 , NAS 1.26:191149
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Plasma sheath effects on ion collection by a pinhole (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The data tabulations presented, which express the results of particle-track trajectories through a simplified plasma-sheath electric field, should prove useful in the assessment of spacecraft 'pinhole-collection' effects. Attention is given to a method accounting for plasma-sheath effects in the application of these results. In addition, scaling rules are given for the application of these calculations to specific cases. A comparison is made between the present model's results and those of recent ion current measurements. Good agreement is obtained.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 93-0567 , ; 11 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Plasma sheath effects on ion collection by a pinhole (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This work presents tables to assist in the evaluation of pinhole collection effects on spacecraft. These tables summarize results of a computer model which tracks particle trajectories through a simplified electric field in the plasma sheath. A technique is proposed to account for plasma sheath effects in the application of these results and scaling rules are proposed to apply the calculations to specific situations. This model is compared to ion current measurements obtained by another worker, and the agreement is very good.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-106098 , E-7740 , NAS 1.15:106098 , AIAA Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A charging study of ACTS using NASCAP (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Charging Analyzer Program (NASCAP) computer code is a three dimensional finite element charging code designed to analyze spacecraft charging in the magnetosphere. Because of the characteristics of this problem, NASCAP can use an quasi-static approach to provide a spacecraft designer with an understanding of how a specific spacecraft will interact with a geomagnetic substorm. The results of the simulation can help designers evaluate the probability and location of arc discharges of charged surfaces on the spacecraft. A charging study of NASA's Advanced Communication Technology Satellite (ACTS) using NASCAP is reported. The results show that the ACTS metalized multilayer insulating blanket design should provide good electrostatic discharge control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-187088 , E-6079 , NAS 1.26:187088 , Fluid Dynamics, Plasma Dynamics, and Lasers Conference; Jun 24, 1991 - Jun 26, 1991; Honolulu, HI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Analysis of Static Spacecraft Floating Potential at Low Earth Orbit (LEO) (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Spacecraft floating potential is the charge on the external surfaces of orbiting spacecraft relative to the space. Charging is caused by unequal negative and positive currents to spacecraft surfaces. The charging process continues until the accelerated particles can be collected rapidly enough to balance the currents at which point the spacecraft has reached its equilibrium or floating potential. In low inclination. Low Earth Orbit (LEO), the collection of positive ion and negative electrons. in a particular direction. are typically not equal. The level of charging required for equilibrium to be established is influenced by the characteristics of the ambient plasma environment. by the spacecraft motion, and by the geometry of the spacecraft. Using the kinetic theory, a statistical approach for studying the interaction is developed. The approach used to study the spacecraft floating potential depends on which phenomena are being applied. and on the properties of the plasma. especially the density and temperature. The results from kinetic theory derivation are applied to determine the charging level and the electric potential distribution at an infinite flat plate perpendicular to a streaming plasma using finite-difference scheme.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 95-1943 , Plasmadynamics and Lasers; Jun 19, 1995 - Jun 22, 1995; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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