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Performance Improvement of Inertial Navigation System Based on Frequency Domain Approaches
주파수 영역 접근방식에 의한 관성항법시스템의 성능향상

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Authors
Chul Woo Kang
Advisor
박찬국
Major
공과대학 기계항공공학부
Issue Date
2014-02
Publisher
서울대학교 대학원
Keywords
Inertial Navigation SystemKalman FilterTransfer AlignmentIntegrated Navigation SystemConing/sculling error
Description
학위논문 (박사)-- 서울대학교 대학원 : 기계항공공학부, 2014. 2. 박찬국.
Abstract
In this dissertation, we discuss a performance improvement method in which frequency domain approaches are applied to an inertial navigation system. The conventional inertial navigation system (INS) algorithm computes all navigation solutions in the time domain. The conventional INS has limitations in it is impossible to resolve some problems by computation in the time domain, such as the observability problem of transfer alignment and the coning/sculling error mitigation algorithm. Thus, frequency domain approaches are applied to resolve the problems.
For the first topic, the frequency domain approach is applied to the transfer alignment method. Typical transfer alignment algorithms estimate the initial attitude and velocity of a projectile using the INS result of the launcher as a measurement. Typical methods have low accuracy for a steady state launcher due to the lack of observability. Thus, a new transfer alignment algorithm using the frequency domain approach is proposed in order to solve observability problem. Amplitude measurements obtained by using a discrete time Fourier transform are applied to transfer alignment algorithm as new measurements and these serve to augment the conventional transfer alignment filter. In simulational results, yaw estimation performance improved with a vibration signal. The proposed algorithm is superior to conventional algorithms in rapid transfer alignment of a steady state vehicle.
For the next topic, a coning/sculling error compensation algorithm is developed. Typical coning and sculling compensation algorithms mitigate the coning and sculling error by using the cross product between inertial sensor measurements. These methods have limitations when applied to vehicles with large coning and sculling errors, because they have theoretical performance limits. Thus, a new direct coning/sculling compensation algorithm is proposed. The continuous coning and sculling error can be expressed by using vibrating parameters such as frequency, amplitude, and phase differences. Our new method uses adaptive notch filtering that estimates the parameters in sinusoidal signals on gyro outputs. If there are continuous sinusoidal signals on gyros, an adaptive notch filter can be used to estimate the parameters of the sinusoidal signals, and a direct coning/sculling compensation algorithm computes the attitude correction term produced by the coning/sculling signal. Our simulation results show that the proposed algorithm works appropriately.
Language
English
URI
http://hdl.handle.net/10371/118380
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Theses (Ph.D. / Sc.D._기계항공공학부)
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