Near Real Time Orbit Detemination of BILSAT-1

Date

2009-06-13

Author

Erdogan, Eren
Karslıoğlu, Mahmut Onur

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

0
downloads

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. Some other Earth's Gravity Models which have been generated recently from the dedicated satellite gravity field missions such as GRACE without including terrestrial observations are also evaluated in the force model for near real time orbit determination. On the other hand, numerical integration methods preferred in GPS based reduced dynamic orbit determination mostly affect the performance of the processor. In this context, another alternative to rigorous implementation of variational equation is the determination of the state transition matrix by using Markley's method which in turn contains only a simplified force model. In this study, BILSAT 1 orbit is evaluated by using EGM2008 and Grace GGM03S Earth gravity models and Markley state transition matrix. GPS based reduced dynamic orbit determination are used as the algorithm. Effect of unmodeled and unknown forces acting on satellite are approximated by first order Gauss Markov Process. Single frequency pseudorange measurements are the observations acquired from SGR 20 spaceborne GPS receiver onboard the BILSAT 1.

Subject Keywords

Reduced Dynamic Orbit Determination, Kalman filter, Markley State Transition Matrix, Spaceborn GPS Receiver, EGM2008, Gauss Markov Process

URI

https://hdl.handle.net/11511/52545

Conference Name

4th International Conference on Recent Advances in Space Technologies

Collections

Graduate School of Natural and Applied Sciences, Conference / Seminar

Suggestions

OpenMETU
Core

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...
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...
An interactive program for GPS-based dynamic orbit determination of small satellites Karslıoğlu, Mahmut Onur (Elsevier BV, 2005-04-01) This work introduces a near real-time dynamic orbit determination program for small satellites. A quality check of orbit data on ground is important for satellites with GPS positioning that is only available at discrete time epochs because of the limited power-supply onboard, so that space-borne GPS receivers are switched on/off intermittently, or because of possible malfunctioning of GPS receivers. The method of parameter estimation with space-borne GPS position fixes as observations is based on an extende...
Long term and safe relative orbit design for heterogeneous spacecraft clusters Yaglioglu, Burak; Tekinalp, Ozan (2021-06-01) The problem of obtaining long term relative orbit configurations for spacecraft clusters with realistic operational considerations such as safety, station keeping and inter-spacecraft distances is addressed. Two different approaches are developed for station keeping and safety objectives. In the first approach, relative orbit configurations, or relative TLEs, are found minimizing deviations from reference mean orbit which would maximize the station-keeping objective. In second one, relative configurations a...
Slow moving target detection for airborne radar systems by dynamic programming on SAR images Gurer, Gorkem; Koc, Sencer; Candan, Çağatay; Orguner, Umut (2019-04-01) A dynamic programming based approach is proposed to detect slow moving, low reflectivity targets for airborne radar systems. The suggested method utilizes the reflectivity amplitudes of the SAR image, possibly containing multiple slow moving targets, and poses the target detection problem as a maximum likelihood sequence detection problem. Dynamic programming is applied to capture the target related features such as along track smeared target signatures in the SAR image to this aim. Typical clutter and targ...

Citation Formats

E. Erdogan and M. O. Karslıoğlu, “Near Real Time Orbit Detemination of BILSAT-1,” presented at the 4th International Conference on Recent Advances in Space Technologies, Istanbul, TURKEY, 2009, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/52545.