Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
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
323
views
377
downloads
Cite This
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
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
E. H. Ata, “Inertial-navıgation-system aiding by combining data link and seeker measurements,” M.S. - Master of Science, Middle East Technical University, 2022.