RAPID INITIALIZATION OF INERTIAL NAVIGATION SYSTEMS THROUGH PARAMETER ESTIMATION

Abstract

The accuracy of an aircraft inertial navigation system depends upon the accuracy with which the system is initially aligned. One procedure for initial alignment involves the use of an external reference. This method utilizes equipment which is much too elaborate for normal operational use. An alternate procedure uses the system's inertial sensors in a self-contained method. If sufficient time were available, the self-contained method could achieve accuracies commensurate with the sensor accuracies; however, in an operational environment it is usually necessary to sacrifice some accuracy in the interest of achieving a more rapid initiation. This dissertation investigates the methods presently available for initialization of an inertial platform in an azimuth wander or free azimuth instrumentation and presents a new method for rapid initialization. The paramount problem is the determination of the initial azimuth angle in minimum time in the presence of random gyro drifts, random accelerometer drifts, and measurement noise.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1970
Accession Number
AD0706219

Entities

People

  • Joseph A. Dasaro

Organizations

  • United States Army Communications-Electronics Command

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes
  • Sensors
  • Space

DTIC Thesaurus Topics

  • Accelerometers
  • Aircrafts
  • Computational Science
  • Control Systems
  • Data Science
  • Differential Equations
  • Electronics Laboratories
  • Engineering
  • Estimators
  • Guidance
  • Inertial Measurement Units
  • Inertial Navigation
  • Inertial Navigation Systems
  • Information Science
  • Kalman Filters
  • Mathematical Filters
  • Navigation

Readers

  • Aerospace Test and Evaluation
  • Control Systems Engineering.
  • Systems Analysis and Design