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
Satellite orbit estimation using kalman filters
Download
index.pdf
Date
2017
Author
İpek, Mehmet
Metadata
Show full item record
Item Usage Stats
520
views
337
downloads
Cite This
In this thesis, satellite orbit determination problem is investigated using various types of Kalman filters based on several ground and space based measurement types. First, the performance of the Gauss' method for initial orbit determination is evaluated and the measurement time separation values required for it to give sufficiently good estimates are determined. Second, filter initialization methods based on a few measurements are proposed for angles only (AE), angles and range (AER), angles and Doppler (AED) and full state observation cases and their performances are investigated. Third, comparison of the relative performances of extended Kalman filter (EKF), unscented Kalman filter (UKF) and continuous-discrete EKF (CD-EKF) is carried out for the sample scenarios assuming that AER and full state measurements are available. It is shown that continuous-discrete EKF running with a reasonable prediction step size, gives the best results in terms of root mean square (RMS) estimation error and computation time. The performance of the CD-EKF is further examined by comparing its RMS errors with posterior Cramer Rao Lower Bound (PCRLB) for all measurement types and it is shown that CD-EKF is almost efficient. In addition to these, relative orbit determination performances obtained using AE, AER and AED measurements are compared. It is shown that the use of the Doppler measurement in addition to angles only measurements significantly improves the estimation performance in terms of position and velocity RMSE's. Furthermore, usefulness of a second observing station (located sufficiently apart from first) is studied. It is found that using a second station provides a significant improvement in the estimation performance especially when the range and Doppler data are not available.
Subject Keywords
Artificial satellites
,
Artificial satellites
,
Artificial satellites
URI
http://etd.lib.metu.edu.tr/upload/12620830/index.pdf
https://hdl.handle.net/11511/26335
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Control of a satellite with flexible smart beam during slew maneuver
Ürek, Halime; Tekinalp, Ozan; Department of Aerospace Engineering (2011)
In this thesis, an attitude control system based on Linear Quadratic Regulator (LQR) technique is developed for a hypothetical Earth observation satellite with a long flexible boom. To improve pointing performance of the satellite, the piezoelectric actuators are used as well. The boom is rectangular made of aluminum with the surface bonded piezoelectric layers on all four surfaces. The boom is modeled using finite elements. The pointing performance of the satellite using various metrics is evaluated throug...
A Control moment gyroscope based on rotational vibrations, dynamic model and experimentation
Arberkli, Ferhat; Azgın, Kıvanç; Department of Mechanical Engineering (2018)
Satellite attitude determination and control system is one of the main subsystems of a spacecraft. Within this domain, there are several types of actuators; such as reaction wheels, control moment gyroscopes (CMG), propulsion systems and magnetic torque rods. All of them are common and currently being used on modern satellites and space stations depending on the application. Conventional reaction wheel and CMG operation are based on the continuous rotation of their rotor mass to exchange angular momentum be...
Orbit determination strategy and verification for geosynchronous satellites
Köker, Abdulkadir; Tekinalp, Ozan; Department of Aerospace Engineering (2019)
In this thesis, the batch and sequential orbit determination procedures for the geostationary satellites are presented. The aim of the study is to investigate the effect of the angle only and standard angle-range measurements on orbit determination accuracy. The effect of various factors on estimation accuracy such as measurement frequency, observation duration, and number of observation sites are investigated using the simulated measurement data. Estimation methods namely, nonlinear least square, extended ...
Determination of sea level trends and vertical land motions from satellite altimetry and tide gauge observations at the Mediterranean Coast of Turkey
Karabil, Sıtar; Karslıoğlu, Mahmut Onur; Demir, Coşkun; Department of Geodetic and Geographical Information Technologies (2011)
A radar altimetry satellite measures the height of sea surface globally. However, tide gauges, measuring Sea Level Height (SLH), are set up on the Earth surface. Hence, SLHs are involved in vertical motion of the Earth crust. In this study, vertical motions of Earth crust have been separated from sea level variations. After clustering of SSH observations with K-means approach, two outlier detection methods Pope and Interquartile (IQR) Tests are implemented in data. Afterwards, each altimetry measurement is ...
GPS-based real-time orbit determination of artificial satellites using kalman, particle, unscented kalman and H-infinity filters
Erdoğan, Eren; Karslıoğlu, Mahmut Onur; Department of Geodetic and Geographical Information Technologies (2011)
Nowadays, Global Positioning System (GPS) which provide global coverage, continuous tracking capability and high accuracy has been preferred as the primary tracking system for onboard real-time precision orbit determination of Low Earth Orbiters (LEO). In this work, real-time orbit determination algorithms are established on the basis of extended Kalman, unscented Kalman, regularized particle, extended Kalman particle and extended H-infinity filters. Particularly, particle filters which have not been applie...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
M. İpek, “Satellite orbit estimation using kalman filters,” M.S. - Master of Science, Middle East Technical University, 2017.