Integrating inertial and satellite navigation systems to improve performance for a maritime search and rescue aircraft


Izet-Ünsalan K., Ünsalan D.

International Conference on Recent Advances in Space Technologies, RAST 2003, İstanbul, Turkey, 20 - 22 November 2003, pp.610-615 identifier

  • Publication Type: Conference Paper / Full Text
  • Volume:
  • Doi Number: 10.1109/rast.2003.1303987
  • City: İstanbul
  • Country: Turkey
  • Page Numbers: pp.610-615
  • Dokuz Eylül University Affiliated: Yes

Abstract

© 2003 IEEE.Inertial Navigation Systems (INS) are vital for airplanes, spacecraft, missiles, surface or subsurface vessels operating at sea where a continuous, accurate and reliable position information, as well as heading, attitude, acceleration and velocity components of the vehicle are provided. Inertial Navigation Systems have the inherent capability of being autonomous; but however, the errors in position coordinates increase unboundedly as a function of time. On the other hand, satellite navigation systems, as well as advanced radio navigation systems, which are available today and which shall be available in the near future, provide very accurate and frequently updated position information. Unfortunately, this data is prone to jamming or being lost due to the limitations of electromagnetic waves, which form the fundamental of their operation. Also, they are not usable for under-sea or under-earth applications. To eliminate these deficiencies, Inertial Navigation Systems are integrated with satellite or hyperbolic navigation systems that also obtain intermittent position information. This study gives a mathematical treatise on such an integrated system. As a feasible example, a Search and Rescue (SAR) aircraft, involved in an expanding area search operation, equipped with a Strapdown Inertial Navigation System and a Global Positioning System is simulated. The inertial navigation system uses two sets of acceleration and rate of rotation sensors. The model used indicates that the error in position information becomes large in time, otherwise it is limited to acceptably low levels if correction information from Global Positioning System is obtained. Improved performance of inertial navigation system by the proposed integration can be utilized to use low-cost sensor elements without the loss of accuracy, thereby making inertial navigation systems a feasible outfit for general purposes.