Ibrahim Oz

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Dr. İbrahim ÖZ is consultant to Turksat AS. He was Vice President of Turksat Satellite Operations and Cable TV Incorporation. He was responsible for operations of Turksat Satellites, generating and uplinking digital television bouquet, procurement and program management of new satellites as well as research, development and satellite design.Prior to his current position, he was satellite control and monitoring director of Turksat AS. He was responsible for operations of Turksat Communication Monitoring Centre to provide its customer continuous and reliable any kind of video, voice or data transmission via Turksat satellites. He was research assistant at Electrical and Electronics Engineering department prior to joining Turksat AS.He received his B.Sc degree in Electrical and Electronics Engineering Department. His M.SC. and PhD degree are also in Electrical and Electronics Engineering.

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Alexander C . T . Geppert

New York University

Armando Marques-Guedes

UNL - New University of Lisbon

Adolfo Chaves Jiménez

Delft University of Technology

Fusun Balik Sanli

Yildiz Technical University

Roland Linck

Bayerisches Landesamt für Denkmalpflege

Harijono Djojodihardjo

Institut Teknologi Bandung

Daniel Condurache

Technical University of Iasi

Aldin Justin

Karunya University

Moriba Jah

The University of Texas at Austin

Kyle DeMars

Texas A&M University

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Thermal Propellant Gauging, SpaceBus 2000 (Turksat 1C) Implementation

by Boris Yendler and Ibrahim Oz

AIAA SPACE 2008 Conference & Exposition, 2008

Knowledge of propellant remaining is one of the most paramount tasks which should be addressed in... more Knowledge of propellant remaining is one of the most paramount tasks which should be addressed in order to complete the mission of GEO satellite successfully. The paper discusses a development and implementation of the thermal propellant gauging system for Turksat 1C (SpaceBus 2000 satellite). Several techniques are typically used to measure the amount of remaining propellant. The bookkeeping, PVT (Pressure, Volume, Temperature) and thermal Propellant Gauging System (PGS) are the most popular methods. Only the thermal PGS method accuracy of propellant estimation increases as propellant load decreases due to increase of temperature rise sensitivity when the tank load decreases. The method can be used for mono or by-propellant propulsion system with one or multiple tank configuration. Implementation of the developed PGS method for Turksat 1C (SpaceBus 2000) satellite is discussed by the current paper. The method consists of several steps, namely, building Tank and Satellite Thermal Models, calibration of the model using current flight data, running the integrated model for several propellant loads for each tank under identical boundary conditions, fitting flight data to simulation results and finding propellant load of the tank. Simulation includes tank temperature change (by heater and/or from sun). Along with propellant estimation, uncertainty analysis is also required in order to determine an error of propellant estimation. The current paper shows that the developed method provides a high accuracy of propellant estimation at EOL. An accurate propellant estimation at EOL is important form business point of view. Knowledge of propellant remaining allows making correct business decisions, like, timely supersinking of a satellite, optimizing profit, avoiding gap in services, etc. The current paper discusses business implications of the PGS method.

Ibrahim Oz

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