ERROR ANALYSIS OF INERTIAL NAVIGATION SYSTEMS | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 43, Volume 2, A.S.A.T. CONFERENCE 21-23 April 1987 , CAIRO, April 1987, Page 1053-1061 PDF (1.24 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.1987.26201 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| M. Samy Abo El Soud1; E. M. Zakzouk1; A. M. Hamad1; M. M. El-Dakiky2 | ||||
| 1Military Technical College, Cairo, Egypt. | ||||
| 2Air Defence College, Alexandria, Egypt . | ||||
| Abstract | ||||
| The accuracy of modern multisensor integrated inertial navigation systems (INS) is affected by various noise sources, such as accelerometer and gyro instabilities. These error sources are often modeled as Gauss-Markov random processes and their effects on navigation system accuracy are determined by covariance simulation. Environmental error sources such as gravity uncertainties have been treated similarly. In this paper, the error equations for a local-level INS are derived. In order to apply covariance error analysis to the system, the linear dynamic error equations in their state-space representation are presented. The error sources considered are gyro drift, accelerometer error, and gravity uncertainties. We have obtained finally a general case model representing error propaga-tion equations including three dimensional free vehicle motion . | ||||
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