TY - JOUR
T1 - Synthetic air data system
AU - Lie, F. Adhika Pradipta
AU - Gebre-Egziabher, Demoz
PY - 2013
Y1 - 2013
N2 - Amethod for estimating the airspeed, angle of attack, and sideslip without using a conventional, pitot-static air data system is presented. The method relies on measurements from Global Positioning System, an inertial measurement unit, and a low-fidelity model of the aircraft's dynamics, which are fused using two cascaded extended Kalman filters. In the cascaded architecture, the first filter uses information from the inertial measurement unit and Global Positioning System to estimate the aircraft's absolute velocity and attitude. These estimates are used as the measurement updates for the second filter in which they are fused with the aircraft dynamics model to generate estimates of the airspeed, angle of attack and sideslip. Methods for dealing with the time and interstate correlation in the measurements coming from the first filter are discussed. Simulation and flight-test results of the method are presented. Simulation results show that the root mean square error of the airspeed estimate is less than 1 m/s. The nominal errors from the flight test on airspeed, angle of attack, and sideslip are less than 2.5 m/s, 2 deg, and 1 deg, respectively. Factors that affect the accuracy, including the implication and impact of using a low-fidelity aircraft model, are discussed.
AB - Amethod for estimating the airspeed, angle of attack, and sideslip without using a conventional, pitot-static air data system is presented. The method relies on measurements from Global Positioning System, an inertial measurement unit, and a low-fidelity model of the aircraft's dynamics, which are fused using two cascaded extended Kalman filters. In the cascaded architecture, the first filter uses information from the inertial measurement unit and Global Positioning System to estimate the aircraft's absolute velocity and attitude. These estimates are used as the measurement updates for the second filter in which they are fused with the aircraft dynamics model to generate estimates of the airspeed, angle of attack and sideslip. Methods for dealing with the time and interstate correlation in the measurements coming from the first filter are discussed. Simulation and flight-test results of the method are presented. Simulation results show that the root mean square error of the airspeed estimate is less than 1 m/s. The nominal errors from the flight test on airspeed, angle of attack, and sideslip are less than 2.5 m/s, 2 deg, and 1 deg, respectively. Factors that affect the accuracy, including the implication and impact of using a low-fidelity aircraft model, are discussed.
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U2 - 10.2514/1.C032177
DO - 10.2514/1.C032177
M3 - Article
AN - SCOPUS:84883276687
SN - 0021-8669
VL - 50
SP - 1234
EP - 1249
JO - Journal of Aircraft
JF - Journal of Aircraft
IS - 4
ER -