20 February 2006 A stellar-inertial navigation scheme
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Proceedings Volume 6041, ICMIT 2005: Information Systems and Signal Processing; 60412F (2006) https://doi.org/10.1117/12.664374
Event: ICMIT 2005: Merchatronics, MEMS, and Smart Materials, 2005, Chongqing, China
Since inertial sensor errors which increase with time are caused by initial orientation error and sensor errors(accelerometer bias and gyro drift bias), the accuracy of these devices, while still improving, is not adequate for many of today's high-precision, long-duration sea, aircraft, and long-range flight missions. This paper presented a navigation error compensation scheme for Strap-Down Inertial Navigation System(SDINS) using Electro-optical sensor. To be specific, SDINS error model and measurement equation were derived, and Kalman filter was implemented. Simulation results show the boundedness of position and attitude errors.
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Jong-bin Yim, Jong-bin Yim, You-chol Lim, You-chol Lim, Joon Lyou, Joon Lyou, } "A stellar-inertial navigation scheme", Proc. SPIE 6041, ICMIT 2005: Information Systems and Signal Processing, 60412F (20 February 2006); doi: 10.1117/12.664374; https://doi.org/10.1117/12.664374


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