Integrated GPS/INS for aerospace application

Farhan A. Faruqi; Kenneth James Turner; Michael B. Pickering

doi:10.1117/12.211503

12 June 1995 Integrated GPS/INS for aerospace application

Farhan A. Faruqi, Kenneth James Turner, Michael B. Pickering

Proceedings Volume 2466, Space Guidance, Control, and Tracking II; (1995) https://doi.org/10.1117/12.211503
Event: SPIE's 1995 Symposium on OE/Aerospace Sensing and Dual Use Photonics, 1995, Orlando, FL, United States

Abstract

The Integrated Global Positioning System (GPS)/Inertial Navigation System (INS) is a cost effective way of providing an accurate and reliable navigation system for civil and military aviation. These systems also provide low cost solutions to mid-course navigation and guidance of medium and long range weapon systems. In this paper an error model is developed which can be used for GPS/INS filter mechanization. It is known that the model has a linear and a non-linear part. The latter consist of a quadratic function of system states and may be approximated by a noise term thereby allowing the use of the well known Kalman Filter (KF) design technique. KF algorithm suitable for this application is also developed, and computer simulation results for a typical aerospace application are given.

Citation Download Citation

Farhan A. Faruqi, Kenneth James Turner, and Michael B. Pickering "Integrated GPS/INS for aerospace application", Proc. SPIE 2466, Space Guidance, Control, and Tracking II, (12 June 1995); https://doi.org/10.1117/12.211503

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