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Thermal Analysis of TRIO-CINEMA Mission

Yoo, Jae-Gun;Jin, Ho;Seon, Jong-Ho;Jeong, Yun-Hwang;Glaser, David;Lee, Dong-Hun;Lin, Robert P.

  • Received : 2011.12.20
  • Accepted : 2012.02.24
  • Published : 2012.03.15

Abstract

Thermal analysis and control design are prerequisite essential to design the satellite. In the space environment, it makes satellite survive from extreme hot and cold conditions. In recent years CubeSat mission is developed for many kinds of purpose. Triplet Ionospheric Observatory (TRIO)-CubeSat for Ion, Neutral, Electron, MAgnetic fields (CINEMA) is required to weigh less than 3 kg and operate on minimal 3 W power. In this paper we describe the thermal analysis and control design for TRIO-CINEMA mission. For this thermal analysis, we made a thermal model of the CubeSat with finite element method and NX6.0 TMG software is used to simulate this analysis model. Based on this result, passive thermal control method has been applied to thermal design of CINEMA. In order to get the better conduction between solar panel and chassis, we choose aluminum 6061-T6 for the material property of standoff. We can increase the average temperature of top and bottom solar panels from $-70^{\circ}C$ to $-40^{\circ}C $ and decrease the average temperature of the magnetometer from $+93^{\circ}C$ to $-4^{\circ}C$ using black paint on the surface of the chassis, inside of top & bottom solar panels, and magnetometer.

Keywords

thermal analysis;thermal control design;CubeSat;picosatellite

References

  1. Gilmore DG, Spacecraft thermal control handbook, volume 1: fundamental technologies, 2nd ed. (Aerospace Press, El Segundo, 2002).
  2. Wertz JR, Larson WJ, Space mission analysis and design, 3rd ed. (Microcosm Press and Springer, New York, 2008), 428-458.

Cited by

  1. On-Orbit Thermal Design and Validation of 1 U Standardized CubeSat of STEP Cube Lab vol.2016, 2016, https://doi.org/10.1155/2016/4213189
  2. Optical Design of a Reflecting Telescope for CubeSat vol.17, pp.6, 2013, https://doi.org/10.3807/JOSK.2013.17.6.533
  3. Functional Verification of Engineering Model of Non-explosive Shockless Holding and Release Mechanism Using Heating Wire Cutting Method vol.23, pp.5, 2013, https://doi.org/10.5050/KSNVE.2013.23.5.401
  4. Construction of a Thermal Vacuum Chamber for Environment Test of Triple CubeSat Mission TRIO-CINEMA vol.30, pp.4, 2013, https://doi.org/10.5140/JASS.2013.30.4.335
  5. Thermal design and analysis of a nanosatellite in low earth orbit vol.115, 2015, https://doi.org/10.1016/j.actaastro.2015.05.012

Acknowledgement

Supported by : National Research Foundation of Korea