A Sensitivity Analysis of the Kalman Filter as Applied to an Inertial Navigation System

Abstract

A tactical missile with mid-course requires the use of an Inertial Navigation System (INS). Steady-state Kalman Filters (SKF) used as estimators have been proposed for use in a Strapdown INS that is considered to be cheaper and easier to implement than a gimbaled INS. This thesis further investigates the sensitivity of the SKF to inaccuracies in the filter parameters such as the dimensional stability derivatives. The analysis is expanded to explore the sensitivity of a system of higher dimension created by the augmentation of an additional state. The study has been performed by independently varying each of the filter parameters over a given range and noting the effect on the accuracy of the filter. One of the benefits of this analysis of the rms estimate errors to variations in the stability derivatives is that it reveals which derivatives need to be accurately determined to ensure stable flight.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1982
Accession Number
ADA119623

Entities

People

  • Gary G. Potter

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Cyber
  • Materials and Manufacturing Processes
  • Sensors
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Computational Science
  • Dead Reckoning
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Estimators
  • Guidance
  • Inertial Navigation
  • Inertial Navigation Systems
  • Kalman Filters
  • Mathematical Filters
  • Measurement
  • Navigation
  • Optimal Estimators
  • Steady State

Readers

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