碩士 / 國立臺北科技大學 / 機電整合研究所 / 96 / Global Position System (GPS) is broadly used in military or civil navigation devices. GPS can work for a long time and its output can still remain stable. But it is easily interfered by external factors such as weather, building and etc.
Inertial Navigation System (INS) doesn’t have the above defects of GPS but its accuracy is reduced by integration errors. Integration errors come from many factors. The errors are mostly caused by output errors and axis misalignment factor. Therefore, calibration and compensation of output errors are required before apply INS. This paper contains state equations of system and the method theory of INS’s calibration and compensation.
The purpose of this paper is to apply Kalman Filter to integrate GPS and INS such that the system can still calculate its position by INS’s signals even if lost GPS signals.
| Identifer | oai:union.ndltd.org:TW/096TIT05651062 |
| Date | January 2008 |
| Creators | Geng-Kwei Chang, 張耕魁 |
| Contributors | 曾百由 |
| Source Sets | National Digital Library of Theses and Dissertations in Taiwan |
| Language | zh-TW |
| Detected Language | English |
| Type | 學位論文 ; thesis |
| Format | 69 |
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