Spacecraft Sheath Modification during Beam Ejection.

Abstract

Numerical solutions to the equations relating the charge ejection to spacecraft potential have been used to study the response of spacecraft potential to ion and electron beam emissions. Ionization occurs within the sheath due to the return current. The charge density and potential profile in the sheath are altered. Non-monotonic behavior of spacecraft potential as a function of beam current is obtained. Parametric studies on the effects of neutral density, electron temperature, mean free path, and spacecraft size have been performed. Experimental evidence of spacecraft sheath modification during beam ejections is discussed. Keywords include: Spacecraft Sheath, Beam Ionization, Spacecraft Charging, and Plasma Simulation.

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Document Details

Document Type
Technical Report
Publication Date
Sep 11, 1985
Accession Number
ADA166604

Entities

People

  • Herbert A. Cohen
  • Shu T.F. Lai
  • William J. Mcneil

Organizations

  • Air Force Research Laboratory

Tags

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Charge Density
  • Classification
  • Ejection
  • Electron Beams
  • Electron Density
  • Electrons
  • Emission
  • Environment
  • Equations
  • Ion Beams
  • Mean Free Path
  • Security
  • Space Charge
  • Spacecraft
  • Spacecraft Charging

Fields of Study

  • Physics

Readers

  • Pulsed Power and Plasma Physics.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Directed Energy
  • Microelectronics
  • Space
  • Space - Hall-Effect Thruster