Performance Tradeoff Study of a GPS-Aided INS for a Rocket Trajectory

Abstract

The Turkish Air Force (TuAF) has started a project to launch a satellite using only Turkish resources. Primary motivation behind this research is to assist TuAF's project by keeping up with these innovations in the navigational arena. The basic challenge in navigation system design is to decide which navigation system (or systems) and implementation techniques will be used, depending on accuracy requirements. The two primary navigation systems that will be integrated in this research are the Inertial Navigation System (INS), and the Global Positioning System (GPS). The Kalman filter algorithm is used to integrate INS and GPS. The rocket (Atlas IIAS launch vehicle) flight profile is generated by using PROFGEN and simulated "true" GPS ephemeris data is incorporated into system as GPS measurements. The "modified" alternative system performance analysis tool, MatSOFE, is utilized in this research study. Standard and differential GPS are compared, as are three different grades of INS, in a tradeoff performance analysis.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2002
Accession Number
ADA423921

Entities

People

  • Muhittin Istanbulluoglu

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Artificial Satellites
  • Computational Science
  • Control Systems
  • Coordinate Systems
  • Global Positioning Systems
  • Inertial Navigation
  • Inertial Navigation Systems
  • Kalman Filters
  • Mathematical Filters
  • Measurement
  • Navigation
  • Spacecraft
  • Three Dimensional
  • Two Dimensional
  • World Geodetic System

Readers

  • Inertial Navigation Systems.
  • Positioning, Navigation, and Timing (PNT) Technology.
  • Team-Based Human-Centered Cognitive Task Decision Making and Information Performance.

Technology Areas

  • Space