Application of Low Thrust Propulsion Techniques to Satellite Attitude Control Systems

Abstract

Equation of motion for a satellite controlled through continuous, low thrust propulsion systems are analyzed through numerical integration techniques. The equations of motion are derived using the Euler Moment Equations. The properties of the satellite model are based upon the Intelsat VII design of communications satellite. A simple rate and error feedback controller is used in providing active attitude control about two and three axes. Perturbation models are created and applied based upon the satellite model. Parameters varied include thrust levels and controller deadband widths. System response times, pointing accuracy, and total impulse required for attitude control are determined as measurements of relative performance.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1991
Accession Number
ADA243890

Entities

People

  • Jeffrey J. Abbott

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Angular Momentum
  • Artificial Satellites
  • Attitude Control Systems
  • Closed Loop Systems
  • Control Systems
  • Differential Equations
  • Electric Propulsion
  • Equations
  • Equations Of Motion
  • Geosynchronous Orbits
  • Numerical Analysis
  • Numerical Integration
  • Propulsion Systems
  • Satellite Orientation
  • Solar Radiation
  • Thrusters

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Space Exploration and Orbital Mechanics.
  • Tactical Satellite Communications Systems Engineering.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Satellites
  • Space - Spacecraft Maneuvers