Orbit determination strategy and verification for geosynchronous satellites

Download

index.pdf

Date

2019

Author

Köker, Abdulkadir

Metadata

Show full item record

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

Item Usage Stats

355
views

107
downloads

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 and unscented Kalman filters are employed and compared. In angle-only estimation, only sequential methods are applied to the simulated angular measurements in order to estimate the position and velocity vectors of a GEO satellite. In standard orbit determination, batch and sequential methods are investigated separately by using both angle and range measurements. The estimation results obtained from simulations for both methods are compared. Finally, the developed batch orbit determination algorithm is compared with the reference software used at TURKSAT ground stations. It is shown that the batch software developed performs as good as if not better than the reference software.

Subject Keywords

Geostationary satellites., Keywords: Orbit Determination, Estimation, Turksat Satellite, Kalman Filter.

URI

http://etd.lib.metu.edu.tr/upload/12624396/index.pdf
https://hdl.handle.net/11511/44347

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Near Real Time Orbit Detemination of BILSAT-1 Erdogan, Eren; Karslıoğlu, Mahmut Onur (2009-06-13) Reduced dynamic models combined with GPSObservations on board the satellites within an extended Kalman Filtering algorithm increases the accuracy of near real time orbit determination. Gravity model as the main force and numerical integration methods are the key concepts in the GPS based reduced dynamic orbit determination. EGM 2008 Earth Gravity Model represented by U.S. National Geospatial Intelligence Agency (NGA) EGM Development Group offers a new model for the determination of gravity accelerations. S...
Satellite orbit estimation using kalman filters İpek, Mehmet; Orguner, Umut; Department of Electrical and Electronics Engineering (2017) 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 (...
ORBIT ESTIMATION STRATEGY FOR LOW EARTH ORBIT AND GEOSTATIONARY SATELLITES Koker, Abdulkadir; Tekinaip, Ozan (2019-01-01) 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 im...
Orbit Control of an Earth Orbiting Solar Sail Satellite Polat, Halis Can; Tekinalp, Ozan (2022-09-01) A concept for the utilization of solar sail satellite's propellant-free thrust capability at Low earth orbit (LEO) is proposed and its orbit control strategy is analyzed. Thrust vector control of the sail's normal direction is used to harvest the solar radiation pressure for generating the necessary acceleration to change the orbital elements. The required control vector direction is determined with two approaches. The first approach is realized by approximating the Gaussian Variational Equations at the emp...
Kinematic orbit determination of low earth orbitsatellites using GPS and Galileo observations Kılıç, Ozan; Karslıoğlu, Mahmut Onur,; Department of Geodetic and Geographical Information Technologies (2019) The GNSS code measurements are used to calculate the orbits of low earth orbiting satellites. Kinematic orbit determination is an approach which is based on satellite to satellite tracking of the GNSS receivers that are mounted onboard the satellites. This approach of orbit determination is independent of satellite dynamics (e.g. gravity field, air-drag etc.) and orbit characteristics (e.g. orbit height, eccentricity etc.) and kinematic precise orbit determination can be subsequently used in gravity field e...

Citation Formats

A. Köker, “Orbit determination strategy and verification for geosynchronous satellites,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.