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

Download

index.pdf

Date

2022-2

Author

Ata, Emre Han

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

246
views

258
downloads

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

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

A method for estimating target velocity and range with passive seeker data Babaoğlu, Buğra Can; Kutay, Ali Türker; Department of Aerospace Engineering (2018) In basic guidance applications, the line-of-sight (LOS) and line-of-sight rate information, which can be provided using a passive seeker, are enough to steer the missile to the target. However, if one wants to augment the guidance algorithm, further information regarding the engagement and/or target is needed. Unlike passive seekers, active and semi-active seekers may provide such information. Nevertheless, if the missile is equipped with a passive seeker, those parameters need to be estimated. Various meth...
Autopilot and guidance algorithms for infrared guided misiles Kılıç, Kayhan Çağlar; Ünver, Baki Zafer; Department of Electrical and Electronics Engineering (2006) Guided missiles are among the most effective threats against air platforms. Aircraft and helicopter losses in the last decades were mostly due to guided missiles, 70% of which were infrared guided missiles. Today, there are as many as 500,000 shoulder-fired missiles in military arsenals around the world, whose guidance algorithms enable them to track the desired trajectories very precisely. In this thesis, main focus is on defining infrared missile guidance and control algorithms in order to study on variou...
Proxy-Based Sliding Mode Stabilization of a Two-Axis Gimbaled Platform Hasturk, Ozgur; Erkmen, Aydan Müşerref; Erkmen, İsmet (2011-10-21) Nowadays, high portion of tactical missiles use gimbaled seekers. For accurate target tracking, the platform where the gimbal is mounted must be stabilized with respect to the motion of the missile body. Line of sight stabilization is critical for fast and precise tracking and alignment. Although conventional PID framework solves many stabilization problems, it is reported that many PID feedback loops are poorly tuned. In this paper, a recently introduced approach, proxy-based sliding mode control to a line...
The stabilization of a two axes gimbal of a roll stabilized missile Hastürk, Özgür; Erkmen, Aydan Müşerref; Department of Educational Sciences (2011) Nowadays, high portion of tactical missiles use gimbaled seeker. For accurate target tracking, the platform where the gimbal is mounted must be stabilized with respect to the motion of the missile body. Line of sight stabilization is critical for fast and precise tracking and alignment. Although, conventional PID framework solves many stabilization problems, it is reported that many PID feedback loops are poorly tuned. In this thesis, recently introduced robot control method, proxy based sliding mode contro...
Thermo-mechanical finite element analysis and design of tail section for a ballistic missile Güler, Togan Kemal; Akkök, Metin; Department of Mechanical Engineering (2012) During the flight of missiles, depending on the flight conditions, rotation of missiles around its centerline can cause instabilities. To override this issue, missile generally is designed in 2 sections. In the missile, the rear tail section and the front section are to rotate freely by means of bearings. Tail section on which bearings are mounted is designed according to thermal loads due to flow of hot gasses through the nozzle and mechanical loads due to inertial load, interference fit and thread preload...

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.