Title :
GPS/INS integration for civil aviation
Author_Institution :
Litton Aero Products, Moorpark, CA, USA
Abstract :
The mechanization equations for generating the INS (inertial navigation system) solution in the proper coordinates are presented. Two different Kalman filter error models for integrating GPS (Global Positioning System) with INS are derived. The model which uses spheroidal component differences rather than Cartesian vector differences is preferable, since it uses error states which can be directly corrected in the INS mechanization equations
Keywords :
aircraft instrumentation; filtering and prediction theory; radionavigation; satellite relay systems; GPS; Global Positioning System; INS; Kalman filter error models; error states; inertial navigation system; mechanization equations; spheroidal component differences; Acceleration; Aerospace control; Computer errors; Drives; Equations; Error correction; Flexible manufacturing systems; Frequency; Global Positioning System; Satellite navigation systems;
Conference_Titel :
Telesystems Conference, 1991. Proceedings. Vol.1., NTC '91., National
Conference_Location :
Atlanta, GA
Print_ISBN :
0-7803-0062-9
DOI :
10.1109/NTC.1991.148022
