Article

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Title

Features of components of spacecraft thermal control systems

Authors

^1,2V.V. Dvirniy, ³G.G. Krushenko, ⁴G.V. Dvirniy, ^1,2A.A. Shevchuk, ⁵M.V. Elfimova, ²M.S. Kuznetsova

Organizations

¹JSC Academician M. F. Reshetnev Information Satellite Systems
Zheleznogorsk, Krasnoyarsk region, Russian Federation
²Siberian Federal University
Krasnoyarsk, Russian Federation
³Institute of Computational Modelling SB RAS, FRC KSC SB RAS
Krasnoyarsk, Russian Federation
⁴Reshetnev Siberian State University of Science and Technology
Krasnoyarsk, Russian Federation
⁵Siberian Fire and Rescue Academy EMERCOM of Russia
Zheleznogorsk, Krasnoyarsk region, Russian Federation

Abstract

The main indicators of the spacecraft quality are their reliability and the period of active existence at orbit, and their temperature regime plays a significant role in this. One of the main tasks of the thermal control system is to ensure a given thermal regime, which ensures the stable operation of all systems within the spacecraft volume. For this, special aggregates are required: pumps for feeding a coolant along a given circuit, fans and others that regulate the collection, transfer and redistribution of heat. Both the thermal control system as a whole and all its aggregates that make it up are subject to high requirements, including in terms of weight and dimensions, guaranteed service life and reliability. We proposed the parameter of perfection of the thermal control system components. The main stages of design, development and experimental testing of spacecraft units are shown. We considered in details the principles of operation and the composition of thermal control systems, especially the basic parameters and the structure of their components which are various types of liquid pumps and low-flow gas fans with low power consumption that provide specified small flow rates and pressures with high reliability within the established period of continuous operation, including using redundancy. As a result of the improvement of the thermal regulation system, along with the improvement of other life support systems, the duration of the active existence of satellites currently reaches 15 years.

Keywords

thermal control system, complementary aggregates, low-flow fans, redundancy, geometric characteristics of blades

References

[1] Istoriya razvitiya otechestvennykh avtomaticheskikh kosmicheskikh apparatov [The history of the development of domestic automatic spacecraft]. Moscow, ООО «Izdatel’skiy dom «Stolichnaya entsiklopediya»», 2015. 752 p. (In Russian)

[2] SESAT (satellite). Available at: http://fakty-o.ru/sesat# (accessed 24.07.2014)

[3] Golovenkin E. N., Dvirniy V. V., Kovalev N. A., Kraev M. V., Ruzanov V. P., Smirnov-Vasil’yev K. G. Agregaty avtonomnykh energeticheskikh sistem : ucheb.posobiye [Assemblies of autonomous energy systems]. Krasnoyarsk, KrPI Publ, 1986. 89 p. (In Russian)

[4] Dvirniy V. V., Kraev M. V. Maloraskhodnyye avtonomnyye nagnetateli [Low consumption self-contained blowers]. Krasnoyarsk, KSU Publ., 1985. 152 p. (In Russian)

[5] Chebotarev V. E., Kosenko V. E. Osnovy proektirovaniya kosmicheskikh apparatov informatsionnogo obespecheniya [Fundamentals of spacecraft design information support]. Krasnoyarsk, SibGAU Publ., 2011, 488 p. (In Russian)

[6] Patraev V. E., Maksimov Ju. V. Metody pojetapnogo obespechenija nadezhnosti bortovoj apparatury kosmicheskih apparatov so srokami aktivnogo dejstvija 10-15 let [Methods for the phased reliability procuring of on-board equipment of the spacecraft with the terms active steps 10-15 years] / Kosmicheskie vehi: sbornik nauchnyh trudov [Space milestone: collection of scientific works]. Krasnoyarsk, IP Suhodol'skaja Ju. Publ., 2009, pp. 445–457. (In Russian)

[7] Testoyedov N. A., Mihnev M. M., Miheev A. E. Tehnologija proizvodstva kosmicheskih apparatov [Production technology of spacecraft]. Krasnoyarsk, SibSAU Publ., 2009, 352 p. (In Russian)

[8] Korolev S. I. Sistemy obespechenija teplovogo rezhima kosmicheskogo apparata [System for thermal regime of the spacecraft], St. Petersburg, BSTU Publ., 2006, 91 p. (In Russian)

[9] Atamasov V. D., Ermolaev V. I., Kukushkin I. O. Sistema obespechenija teplovogo rezhima kosmicheskogo apparata [System for thermal regime of the spacecraft]. St. Petersburg, MO RF Publ., 2003, 71 p. (In Russian)

[10] Jani J. M., Leary M., Subic A., Gibson M. A review of shape memory alloy research, applications and opportunities // Materials & Design, 2014, vol. 56, pp. 1078-1113.

[11] Qidwai M. A., Lagoudas D. C. On thermomechanics and transformation surfaces of polycrystalline NiTi shape memory alloy material // International Journal of Plasticity, 2000, vol. 16, issue 10-11, pp. 1309-1343.

For citing this article

Dvirniy V.V., Krushenko G.G., Dvirniy G.V., Shevchuk A.A., Elfimova M.V., Kuznetsova M.S. Features of components of spacecraft thermal control systems // Spacecrafts & Technologies, 2019, vol. 3, no. 1, pp. 13-21. doi: 10.26732/2618-7957-2019-1-13-21

This Article is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License (CC BY-NC 4.0).