Design of Thermal Control Subsystem for TUSAT Telecommunication Satellite
TUSAT is a prospective Turkish
Communication Satellite designed for providing mainly data
communication and broadcasting services through Ku-Band
and C-Band channels. Thermal control is a vital issue in
satellite design process. Therefore, all satellite subsystems and
equipments should be maintained in the desired temperature
range from launch to end of maneuvering life. The main
function of the thermal control is to keep the equipments and
the satellite structures in a given temperature range for various
phases and operating modes of spacecraft during its lifetime.
This paper describes the thermal control design which uses
passive and active thermal control concepts. The active
thermal control is based on heaters regulated by software via
thermistors. Alternatively passive thermal control composes of
heat pipes, multilayer insulation (MLI) blankets, radiators,
paints and surface finishes maintaining temperature level of
the overall carrier components within an acceptable value.
Thermal control design is supported by thermal analysis using
thermal mathematical models (TMM).
[1] Gilmore, D. G., Spacecraft Thermal Control Handbook Volume I:
Fundamental Technologies, 2nd ed., The Aerospace Press, California,
2002.
[2] Karam, R. D., Satellite Thermal Control for Systems Engineer.,
Vol.181, AIAA, Reston, VA, 1998.
[3] Koedinger, M., and Brissonnaud, T., "SPACEBUS 3000- Thermal
Control ARABSAT 2," Proceedings of the Sixth European Symposium
on Space Environmental Control Systems, European Space Agency ,
Nordwijk, the Netherlands, 1997, pp. 57-66.
[4] Sacchi, E., and Massa, T ., "The Termal Control of Artemis Spacecraft,"
Proceedings of the Sixth European Symposium on Space Environmental
Control Systems, European Space Agency , Nordwijk, the Netherlands,
1997, pp. 49-56.
[5] Hwangbo, H., and Chul Kim, W., "design of Thermal Control for
Koreasat 3 Communication Satellite," 33 rd Thermophysics Conference,
28 June-1 July 1999, Norfolk, VA, 1999.
[6] Murat Bulut, Nedim Sozbir and S. Gulgonul, "Thermal Control Design
of Tusat", 6th. International Energy Conversion Engineering Conference
(IECEC), Cleveland, OH, July 28-30, 2008.
[7] Murat Bulut, Selman Demirel, Nedim Sozbir and S. Gulgonul, "Battery
Thermal Design Conception of Turksih Satellite", 6th. International
Energy Conversion Engineering Conference (IECEC), Cleveland, OH,
July 28-30, 2008.
[1] Gilmore, D. G., Spacecraft Thermal Control Handbook Volume I:
Fundamental Technologies, 2nd ed., The Aerospace Press, California,
2002.
[2] Karam, R. D., Satellite Thermal Control for Systems Engineer.,
Vol.181, AIAA, Reston, VA, 1998.
[3] Koedinger, M., and Brissonnaud, T., "SPACEBUS 3000- Thermal
Control ARABSAT 2," Proceedings of the Sixth European Symposium
on Space Environmental Control Systems, European Space Agency ,
Nordwijk, the Netherlands, 1997, pp. 57-66.
[4] Sacchi, E., and Massa, T ., "The Termal Control of Artemis Spacecraft,"
Proceedings of the Sixth European Symposium on Space Environmental
Control Systems, European Space Agency , Nordwijk, the Netherlands,
1997, pp. 49-56.
[5] Hwangbo, H., and Chul Kim, W., "design of Thermal Control for
Koreasat 3 Communication Satellite," 33 rd Thermophysics Conference,
28 June-1 July 1999, Norfolk, VA, 1999.
[6] Murat Bulut, Nedim Sozbir and S. Gulgonul, "Thermal Control Design
of Tusat", 6th. International Energy Conversion Engineering Conference
(IECEC), Cleveland, OH, July 28-30, 2008.
[7] Murat Bulut, Selman Demirel, Nedim Sozbir and S. Gulgonul, "Battery
Thermal Design Conception of Turksih Satellite", 6th. International
Energy Conversion Engineering Conference (IECEC), Cleveland, OH,
July 28-30, 2008.
@article{"International Journal of Electrical, Electronic and Communication Sciences:53858", author = "N. Sozbir and M. Bulut and M.F.Oktem and A.Kahriman and A. Chaix", title = "Design of Thermal Control Subsystem for TUSAT Telecommunication Satellite", abstract = "TUSAT is a prospective Turkish
Communication Satellite designed for providing mainly data
communication and broadcasting services through Ku-Band
and C-Band channels. Thermal control is a vital issue in
satellite design process. Therefore, all satellite subsystems and
equipments should be maintained in the desired temperature
range from launch to end of maneuvering life. The main
function of the thermal control is to keep the equipments and
the satellite structures in a given temperature range for various
phases and operating modes of spacecraft during its lifetime.
This paper describes the thermal control design which uses
passive and active thermal control concepts. The active
thermal control is based on heaters regulated by software via
thermistors. Alternatively passive thermal control composes of
heat pipes, multilayer insulation (MLI) blankets, radiators,
paints and surface finishes maintaining temperature level of
the overall carrier components within an acceptable value.
Thermal control design is supported by thermal analysis using
thermal mathematical models (TMM).", keywords = "Spacecraft thermal control, design of thermal
control.", volume = "2", number = "7", pages = "1384-4", }