Small Satellite Attitude Control for Sun-Oriented Operations Utilizing a Momentum Bias With Magnetic Actuators.

Abstract

The feasibility of using a three axis control, momentum bias system with magnetic actuators for sun-oriented operations is explored. Relevant equations of motion are developed for a sun-oriented coordinate system and control laws are developed for: initial spacecraft capture after launch vehicle separation; reorientation from Earth oriented to a sun oriented operations mode; sun-oriented attitude control; and momentum wheel control. Simulations demonstrating the stability and time responsiveness of the system are performed. Sensor noise input tests are performed to investigate the systems susceptibility to imperfect conditions. Cross product of inertia effects are also input to test for system instability.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1995
Accession Number
ADA297796

Entities

People

  • Scott M. Wolfe

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Sensors
  • Space

DTIC Thesaurus Topics

  • Artificial Satellites
  • Astronautics
  • Control Systems
  • Equations Of Motion
  • Launch Vehicles
  • Magnetic Detectors
  • Magnetic Fields
  • Measurement
  • Momentum
  • Satellite Attitude Control
  • Satellite Buses
  • Simulations
  • Small Satellites
  • Solar Panels
  • Solar Radiation
  • Space Systems
  • Spacecraft

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers