Attitude Determination of a Three-Axis Stabilized Spacecraft Using Star Sensors

Abstract

The purpose of this thesis is to investigate the application of a six-state discrete Kalman filter for estimates of angular rates based solely on star sensor data. The satellite is in a Molnyia orbit where orbital angular velocity and orbital angular acceleration are predetermined and stored in the on-board computer; such that they will be available each time a star observation is made. A two-axis star sensor will provide two angles to the estimator whereupon the third "unsensed" angle will be predicted; the rates about all three axes are then estimated. The results show that the rate estimates are accurate to within 10(exp -7) r/s, which is equivalent to the data produced by gyroscopes.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1999
Accession Number
ADA374426

Entities

People

  • Jay D. Vogt

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Sensors
  • Space

DTIC Thesaurus Topics

  • Algorithms
  • Angular Acceleration
  • Angular Momentum
  • Artificial Satellites
  • Astronautics
  • Attitude Control Systems
  • Computers
  • Control Systems
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Estimators
  • Grids
  • Measurement
  • Observation
  • Spacecraft
  • Star Trackers

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Inertial Navigation Systems.

Technology Areas

  • Space
  • Space - Orbital Debris
  • Space - Spacecraft Maneuvers