Attitude Determination Using Star Tracker Data with Kalman Filters

Abstract

This study adapts some established attitude determination techniques for use with star tracker measurements on satellites. Other work in this area has utilized gyro measurements with star tracker updates. Today's star trackers are giving measurements with accuracies of less than 6 arcseconds, and are therefore of high enough fidelity to be used alone. Computer simulation of a Linear Kalman Filter to process these measurements is presented. The Filter uses a linear, constant coefficient state matrix with the Optimal Control Law to provide negative feedback control. The control law uses information developed through the equations of motion of the spacecraft in a Molnyia orbit. Modifications to the Filter, including glitch rejection and various covariance manipulation techniques are discussed as possible sources for performance enhancement.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 2001
Accession Number
ADA401577

Entities

People

  • Henry D. Travis

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Abstracts
  • Accuracy
  • Algorithms
  • Artificial Satellites
  • C Programming Language
  • Coefficients
  • Computer Programming
  • Electrical Engineering
  • Equations
  • Equations Of Motion
  • Filters
  • Kalman Filters
  • Measurement
  • Simulations
  • Space Systems
  • Spacecraft
  • Star Trackers

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Inertial Navigation Systems.

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers