Thermal Conduction Measurement and Analysis for a Spaceborn Sensor

Abstract:

The present study is aimed at investigating the thermal conduction characteristics of a spaceborn sensor experimentally and computationally. The experimental measurement has been carried out in a high vacuum chamber with twenty selected thermal couples attached to the sensor module. The detailed internal thermal control design, material for heat release, temperature limit, and control logic of the sensor assembly have been described in the study. The total thermal resistance for the sensor has been evaluated from the experimental results of the steady state temperature distributions under a heat power of 5.5 W and the sensor heater power modulation has been obtained to keep the PT1000 within the accepted temperature range. Under the assumed temperature boundary conditions, the measured thermal resistances and the modulated sensor heater power, the maximum PT1000 temperature distribution is found to be 25.26 °C ± 3.44 °C with the finite element analysis. Heat loss has been evaluated for the invar mount of the sensor module. In addition, the overall orbit peak and average heater powers needed are 4.61 W and 1.61 W respectively.

• Periodical: Key Engineering Materials (Volumes 656-657)
• Pages: 741-746
• DOI: https://doi.org/10.4028/www.scientific.net/KEM.656-657.741
• Online since: July 2015
• Authors: Chia Yen Chan*, Bill Wang, Chien Pao Lin, Tom Hsiao, Ting Ming Huang
• Keywords: Finite Element Analysis (FEA), Sensor Heater Power, Spaceborn Sensor, Thermal Resistance Measurement

References

[1] D. G. Gilmore, Spacecraft thermal control handbook volume I: Fundamental Technologies, 2nd ed., The Aerospace Press, California, (2002).

[2] D. Dooling, M. M. Finckenor, Material selection guidelines to limit atomic oxygen effects on spacecraft surfaces, NASA/TP-1999-209260, Marshal Space Flight Center, MSFC, Alabama 35812, (1999).

[3] A. Anvari, K. S. Niaki and F. Farhani, Numerical investigation on the effect of radiator position on temperatures of small satellite components, Proceedings of The 14th Annual (International) Mechanical Engineering Conf. (ISME2006), Tehran–Iran, (2006).

[4] A. Nazari, H. Emami, Thermal control and thermal sensors of observation satellite, The International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences. Vol. XXXVII. Part B2. Beijing, 2008, pp.949-952.

[5] A. Anvari, F. Farhani and K. S. Niaki, Comparative study on space qualified paints used for thermal control of a small satellite, Iranian Journal of Chemical Engineering, 6 (2009), 50-62.

[6] N. Sozbir, M. Bulut, M. F. Oktem, A. Kahriman and A. Chaix, Design of thermal control subsystem for TUSAT telecommunication satellite, World Academy of Science, Engineering and Technology 19 (2008), 395-398.

[7] M. Bulut, N. Sozbir and S. Gulgonul, Thermal control design of Tusat, 6th. International Energy Conversion Engineering Conference (IECEC), Cleveland, 2008, pp.28-30.

DOI: 10.2514/6.2008-5751