INS/GPS Integration Architectures

Abstract

An inertial navigation system (INS) exhibits relatively low noise from second to second, but tends to drift over time. Typical aircraft inertial navigation errors grow at rates between 1 and 10 nmi/h (1.8 to 18 km/h) of operation. In contrast, Global Positioning System (GPS) errors are relatively noisy from second to second, but exhibit no long-term drift. Using both of these systems is superior to using either alone. Integrating the information from each sensor results in a navigation system that operates like a drift-free INS. There are further benefits to be gained depending on the level at which the information is combined. This presentation will focus on integration architectures, including loosely coupled, tightly coupled, and deeply integrated configurations. (Deep integration is trademarked by Draper Laboratory.) The advantages and disadvantages of each level of integration will be listed. Examples of current and future systems will be cited.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2010
Accession Number
ADA581020

Entities

People

  • George T. Schmidt
  • Richard E. Phillips

Organizations

  • Massachusetts Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Accelerometers
  • Accuracy
  • Algorithms
  • Artificial Satellites
  • Coordinate Systems
  • Correlators
  • Detectors
  • Estimators
  • Guidance
  • Inertial Measurement Units
  • Inertial Navigation
  • Inertial Navigation Systems
  • Kalman Filters
  • Low Noise
  • Measurement
  • Navigation
  • Vehicles

Readers

  • Inertial Navigation Systems.
  • Systems Analysis and Design

Technology Areas

  • Space