Realtime Differential GPS (Global Positioning System) offers precise positioning capabilities. This can be achieved by combination of code and phase measurements with transmitted correction terms from a ground reference via link to the moving receiver e.g., in an aircraft. Although tight ICAO (International Civil Aviation Organization) limits for precision approaches or taxi guidance can be met, this system needs a complement to compensate insufficiencies, for example in dynamic maneuvers or total failure of position information due to satellite masking. Using International Measurement Units (IMU) with good dynamic characteristics but longterm drift as a result of misalignment, accelerometer and gyro errors, Kalman filter techniques are used to predict and eliminate these errors. Loss of GPS position due to jamming, satellite shadowing dynamic influences leads to a decreasing filter accuracy, if the GPS position is taken as reference (measurement vector) for the Kalman filter. Therefore a filter concept which is sustained by uncorrelated range and range rate measurements is discussed. Several investigations by means of simulation and flight tests show that the strategy chosen is able to perform precise position and attitude information. Even under dynamic environment with separated satellite masking an accuracy to meet the tight limits for precision approaches can be fulfilled.
Precise Flight Navigation by Integration of Global Positioning System and Inertial Measurement Units
1992
6 pages
Report
No indication
English
Precise flight navigation by integration of global positioning system & inertial measurement units
British Library Online Contents | 1992
|Global positioning systems, inertial navigation, and integration
TIBKAT | 2001
|Global positioning systems, inertial navigation, and integration
TIBKAT | 2007
|Combining Inertial Navigation System With GPS Precise Point Positioning: Flight Test Results
British Library Conference Proceedings | 2006
|