Development of a tool for prediction of the orbital parameters of earth observation satellites

Date

2007-06-16

Author

Altay, Alkan
Karsli, Gizem
Oezkan, Ahmet

Metadata

Show full item record

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

Item Usage Stats

201
views

0
downloads

Development of a tool that predicts the orbital parameters of a satellite from an initial state vector for a specified time interval is addressed. The elements used in the algorithm are presented. The prediction performance of the algorithm is demonstrated by using the two line elements of a GPS satellite and the CHAMP scientific satellite.

Subject Keywords

Artificial satellites, Prediction algorithms, Aerospace industry, Position measurement, Military satellites, Space technology, Extraterrestrial measurements, Velocity measurement, Satellite ground stations, Performance evaluation

URI

https://hdl.handle.net/11511/67264

DOI

https://doi.org/10.1109/rast.2007.4284020

Collections

Unclassified, Conference / Seminar

Suggestions

OpenMETU
Core

A ground-based orbit determination for BILSAT Karslıoğlu, Mahmut Onur; Friedrich, J; Urhan, H (2005-06-11) This paper describes a ground-based orbit determination algorithm for the remote sensing satellite BILSAT. A near-real time quality control of orbit data in the ground station is of vital importance to detect outliers or to bridge data gaps where position information is not available. These might result both from possible temporary mal-functioning and intermittently on/off switching of the onboard GPS receiver. A dynamic approach is preferred for the orbit determination because it includes not only outlier'...
Development of a State Dependent Riccati Equation Based Tracking Flight Controller for an Unmanned Aircraft Tekinalp, Ozan (2013-08-22) A dual loop nonlinear State Dependent Riccati Equation (SDRE) control method is developed for the flight control of an unmanned aircraft. The outer loop addresses the attitude and altitude kinematics, while the inner loop handles the translational and rotational equations of motion. The control strategy utilizes a tracking control problem. The mismatch due to the SDC factorization of the inner loop is handled with a nonlinear compensator again derived from the tracking control formulation. The quadratic opt...
Design and simulation of nana-optical beam generators based on zero-index materials Eris, Ozgur; Abanuzoglu, Tutku; Ergül, Özgür Salih (2019-09-01) We present design and computational analysis of near-zero-index (NZI) structures that act as nano-optical beam generators when excited internally by isotropic sources. The designed structures have homogenized shell geometries with various modifications to generate asymmetric tridirectional, bidirectional, and unidirectional beams, in addition to symmetric ones. NZI properties make it possible to generate beams from planar surfaces, while numerical results show that the behavior of a shell is very sensitive ...
In-orbit estimation of time-varying residual magnetic moment for small satellite applications Söken, Halil Ersin (2013-09-16) A method for in-orbit estimation of time-varying residual magnetic moment is presented for small satellite applications. The Unscented Kalman Filter is used as the estimator. Unlike the existing studies in the literature, unexpected abrupt changes in the residual magnetic moment are also considered. Sudden shifts in the mean of the residual magnetic moment is detected by a low pass filter applied to the normalized innovation of the Unscented Kalman Filter. Then, by using a simple approach, which does not re...
Development of state dependent factorized optimal control methods with application to spacecraft coulomb formations Gomroki, Mohammad Mehdi; Tekinalp, Ozan; Topputo, Francesco; Department of Aerospace Engineering (2017) Among spacecraft formation control techniques, Coulomb tether to control the relative distance is proposed in the literature. A Coulomb tether is similar to physical tether that uses coulomb forces to keep spacecraft at close proximity. It is indicated that a coulomb tether provides an almost a propellantless formation control. The charges loaded to the bodies, can create attractive and repulsive forces between these bodies. Since the forces are relative, coulomb forces cannot change the total linear or ang...

Citation Formats

A. Altay, G. Karsli, and A. Oezkan, “Development of a tool for prediction of the orbital parameters of earth observation satellites,” 2007, p. 393, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/67264.