This thesis addresses the problem of determining aircraft position during flight given noisy and biased measurements from a barometric altimeter and two tactical air navigation (TACAN) transceivers. A Kalman smoother is developed to perform post-flight data processing on the measurement data. The smoother estimates aircraft position, velocity, and acceleration as well as biases in the measurements. Since actual flight test data is not available, computer simulations examine the performance of this tracking technique. The simulated flight includes low and high-speed turns, constant rate ascents, descents, and accelerations. The tracking algorithm tracked the aircraft inertial navigation system used by the 4950th Test Wing in another flight test program showed a position error growth rate of 2000 meters per hour. (RH)
Aircraft Tracking with Dual TACAN
1988
71 pages
Report
No indication
English
Avionics , Navigation, Guidance, & Control , Altimeters , Flight simulation , Inertial navigation , Position(Location) , TACAN , Tracking , Acceleration , Aircraft , Algorithms , Ascent trajectories , Barometric pressure , Bias , Computerized simulation , Data processing , Errors , Estimates , Experimental data , Flight , Flight testing , Growth(General) , Measurement , Rates , Transmitter receivers , Theses
Emerald Group Publishing | 1985
Tema Archive | 1975
|Elektronische TACAN-Schiffsantenne
Tema Archive | 1975
|Tema Archive | 1978
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