Flight Test Data Analysis of a Low Cost GPS/IMU Integrated Navigation System

Min-I James Chang

Abstract:	Flight tests have been conducted to demonstrate the performance of a GPS receiver and strapdown inertial sensor integrated navigation system. A 15 state suboptimal Kalman filter was designed for inflight alignment and the calibration of the inertial sensor error sources. The estimated navigation errors are applied to correct the strapdown navigation solution and the estimated inertial sensor errors were used to update the inertia1 sensor measurement calibration coefficients in real time. The post flight test data analysis showed that the performance of the suboptimal Kalman filter was satisfactory, Carouse1 IV output verified that the multisensor navigation unit was being calibrated within the factory design specifications. Flight test results show that a low cost INS with the aid of GPS measurements can provide long term high accuracy navigation solutions.
Published in:	Proceedings of the 47th Annual Meeting of The Institute of Navigation (1991) June 10 - 12, 1991 Williamsburg Hilton and National Conference Center Williamsburg, VA
Pages:	167 - 173
Cite this article:	Chang, Min-I James, "Flight Test Data Analysis of a Low Cost GPS/IMU Integrated Navigation System," Proceedings of the 47th Annual Meeting of The Institute of Navigation (1991), Williamsburg, VA, June 1991, pp. 167-173.
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