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
ORBIT ESTIMATION STRATEGY FOR LOW EARTH ORBIT AND GEOSTATIONARY SATELLITES
Date
2019-01-01
Author
Koker, Abdulkadir
Tekinaip, Ozan
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
174
views
0
downloads
Cite This
In this paper, an orbit determination strategy that uses non-recursive batch filter, and unscented Kalman filter methods is presented and utilized for satellite orbit determination. For the orbit determination system, the range, azimuth, and elevation angles of the satellite measured from ground tracking stations are used for observations. An efficient filter initialization algorithm using the Gibbs method is also proposed to provide an initial state estimate. The non-recursive batch filter is applied to improve initial conditions and to provide initial covariance. Finally, the unscented Kalman filter is used for recursive nonlinear estimation of the states of an Earth-orbiting satellite. The effect of measurement noise and observation duration on orbit determination accuracy is also investigated, and presented.
URI
https://hdl.handle.net/11511/65713
http://amz.xcdsystem.com/A464D031-C624-C138-7D0E208E29BC4EDD_abstract_File10296/FinalPaper_AAS-18-365_0910105709.pdf
Collections
Department of Aerospace Engineering, Conference / Seminar
Suggestions
OpenMETU
Core
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 ...
Orbital and spin phase-resolved spectroscopy of the intermediate polar EX Hya using XMM-Newton data
Pekon, Y.; Balman, Şölen (Oxford University Press (OUP), 2011-02-01)
We present the orbital phase-resolved spectra of an intermediate polar, EX Hya, together with the spin phase-resolved spectra during two different epochs using the X-ray Multi-Mirror Mission (XMM-Newton), European Photon Imaging Camera (pn instrument). We find that the source at the two epochs has the same X-ray luminosity of similar to 6.5 x 1031 erg s-1. We detect spectral variations between the 2000 and 2003 observations of the source. We fitted the spectrum using a neutral hydrogen absorption model with...
GPS-Based Real-Time Orbit Determination of Low Earth Orbit Satellites Using Robust Unscented Kalman Filter
Karslıoğlu, Mahmut Onur; Erdogan, Eren; Pamuk, Onur (2017-11-01)
In this research, a novel algorithm for real-time orbit determination (RTOD) is presented using the robust unscented Kalman filter (RUKF) with global positioning system (GPS) group and phase ionospheric correction (GRAPHIC) observables. To increase the reliability of the solution, a robust approach is included in the UKF to cope with the bad, invalid, or degraded measurements leading to the divergence or inaccurate output of the filter. Robustness is provided by making the filter less sensitive to faulty me...
CMOS LNA design for LEO space S-Band applications
Telli, A; Askar, M (2003-05-07)
In this study, LNAs for low earth orbit (LEO) S-Band uplink/downlink "System-on-Chip" receiver stages with different topologies are designed and simulated using the Mietec CMOS 0.7mum process and the Cadence/BSIM3v3 tool.
Radar cross section analysis by shooting and bouncing rays method
Çakır, Mustafa Kağan; Tokdemir, Turgut; Department of Engineering Sciences (2015)
In this study, a MATLAB code incorporating `Shooting and Bouncing Rays (SBR) Method` is developed for calculating Radar Cross Section (RCS) of complex shapes. The code can calculate ray paths, magnetic current sheets, incident and scattered electric fields and RCS in horizontal, vertical and cross polarizations. While reflection effects are calculated by SBR algorithm, diffraction effects due to edges and corners are handled by `Equivalent Edge Currents (EEC’s)`. Wave frequency, aspect angle and number of r...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
A. Koker and O. Tekinaip, “ORBIT ESTIMATION STRATEGY FOR LOW EARTH ORBIT AND GEOSTATIONARY SATELLITES,” 2019, vol. 167, p. 2859, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/65713.