GPS/INS integration for civil aviation

Author

Diesel, John W.

Author_Institution

Litton Aero Products, Moorpark, CA, USA

fYear

1991

fDate

26-27 Mar 1991

Firstpage

223

Lastpage

228

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;

fLanguage

English

Publisher

ieee

Conference_Titel

Telesystems Conference, 1991. Proceedings. Vol.1., NTC '91., National

Conference_Location

Atlanta, GA

Print_ISBN

0-7803-0062-9

Type

conf

DOI

10.1109/NTC.1991.148022

Filename

148022

Link To Document

https://search.isc.ac/dl/search/defaultta.aspx?DTC=49&DC=3554805