TY - GEN
T1 - A GNSS/IMU-based 5-hole pitot tube calibration algorithm
AU - Sun, Kerry
AU - Regan, Chris
AU - Gebre Egziabher, Demoz
PY - 2019/1/1
Y1 - 2019/1/1
N2 - An algorithm for calibrating a five-hole Pitot tube in-situ using measurement from a GNSS receiver and IMU is presented. Since GNSS and IMU are standard sensors on most modern aircraft including small UAVs, the algorithm has the promise of simplifying the process of calibrating Pitot tubes by obviating the need for special instrumentation during flight tests. The algorithm is a cascaded, two-stage, batch estimator which uses the ground speed and attitude solution from the fusion of GNSS and an IMU as a reference. A method for the design and analysis of flight test trajectories to yield more accurate calibration results is discussed. The algorithm is validated on the data from the two flight tests, and those tests are conducted using an UltraStick 120 UAV. The mean square error (MSE) of airspeed using the linear method in stage 1 is 0.1278 m/s and 1.0510 m/s for each flight respectively. The error bounds of angle-of-attack and-sideslip in stage 2 are 0.2405 degrees and 0.1476 degrees for Fight Test 1, and 1.3982 degrees and 0.0322 degrees for Flight Test 2 respectively.
AB - An algorithm for calibrating a five-hole Pitot tube in-situ using measurement from a GNSS receiver and IMU is presented. Since GNSS and IMU are standard sensors on most modern aircraft including small UAVs, the algorithm has the promise of simplifying the process of calibrating Pitot tubes by obviating the need for special instrumentation during flight tests. The algorithm is a cascaded, two-stage, batch estimator which uses the ground speed and attitude solution from the fusion of GNSS and an IMU as a reference. A method for the design and analysis of flight test trajectories to yield more accurate calibration results is discussed. The algorithm is validated on the data from the two flight tests, and those tests are conducted using an UltraStick 120 UAV. The mean square error (MSE) of airspeed using the linear method in stage 1 is 0.1278 m/s and 1.0510 m/s for each flight respectively. The error bounds of angle-of-attack and-sideslip in stage 2 are 0.2405 degrees and 0.1476 degrees for Fight Test 1, and 1.3982 degrees and 0.0322 degrees for Flight Test 2 respectively.
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U2 - 10.2514/6.2019-0360
DO - 10.2514/6.2019-0360
M3 - Conference contribution
SN - 9781624105784
T3 - AIAA Scitech 2019 Forum
BT - AIAA Scitech 2019 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2019
Y2 - 7 January 2019 through 11 January 2019
ER -