Inertial-navıgation-system aiding by combining data link and seeker measurements

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2022-2

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Ata, Emre Han

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Missiles are equipped with seekers to increase the probability of intercepting the target. A gimballed seeker provides gimbal angles and rates used in a guidance law. Conventionally, the seeker is used at the terminal phase only. However, the seeker can also be used at the midcourse phase to eliminate inertial navigation system (INS) errors. Some missiles are also equipped with the data link to communicate with the platform. This data link provides data such as the image acquired by the seeker to the platform screen. The data link also offers range information between platform and missile, which can be used to increase the quality of INS solutions. In this thesis, a seeker and a data link are used to improve the INS solution. The INS errors are estimated by the Extended Kalman Filter (EKF). The attitude errors are not included in this study to make the system and analysis easier. Measurement models for the seeker gimbal angles and the data link range are derived. The proposed methodology does not require maneuver or the knowledge of the landmark position.

Subject Keywords

INS error estimation, Extended Kalman Filter, Bearing-only tracking, Data link range measurement

URI

https://hdl.handle.net/11511/96384

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Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

E. H. Ata, “Inertial-navıgation-system aiding by combining data link and seeker measurements,” M.S. - Master of Science, Middle East Technical University, 2022.