Passive cooling system designing for a spacecraft onboard complex

Aeronautical and Space-Rocket Engineering

Design, construction and manufacturing of flying vehicles


DOI: 10.34759/vst-2021-2-96-106

Аuthors

Shilkin O. V.1*, Kishkin A. A.2**, Zuev A. A.2***, Delkov A. V.2****, Lavrov N. A.3

1. Compani «Information satellite systems of academician M.F. Reshetnev», 52, Lenin str., Zheleznogorsk, Krasnoyarsk region, 662972, Russia
2. Siberian State University of Science and Technology named after academician M.F. Reshetnev, 31, Krasnoyarsky Rabochy av., Krasnoyarsk, 660014, Russia
3. Bauman Moscow State Technical University, MSTU, 5, bldg. 1, 2-nd Baumanskaya str., Moscow, 105005, Russia

*e-mail: shilkin@iss-reshetnev.ru
**e-mail: spsp99@mail.ru
***e-mail: dla2011@inbox.ru
****e-mail: delkov-mx01@mail.ru

Abstract

The presented work considers the passive part designing for the cooling system of the spacecraft onboard complex.

The equipment of cryogenic and helium temperatures level, necessary for ensuring standard operation conditions [3, 4] characteristic for the deep space, external solar radiation and instrument-hardware electromagnetic emissions, is frequently employed in thermal control systems, ensuring the thermal mode [2], for the state-of-the-art space platforms [1]. The telescope being designed will be capable of operating in both the single telescope mode and as a part of the interferometer between the “Earth-Space” bases (with ground-based telescopes). The telescope operation range is from 20 microns to 17 mm [5–7].

The observatory is planned to operate for three years with the reflector temperature of 4.5 K, and then for another 7–10 years with the total temperature of 50 K [8]. The term of the observatory active life is ten years. The reflector thermal mode sustaining is being implemented by the observatory cooling system, consisting of passive screens and Stirling and Joule-Thomson cryogenic machines.

The thermal model and the design scheme are being considered on the example of the passive cooling system of the onboard complex of the “Millimetron” observatory scientific equipment. The general cooling system includes both the active part, represented by the heat exchange units, removing heat from the cryoscreen and equipment to the Joule-Thomson and Stirling machines, and the passive part, represented by the protective screens system and reflective surfaces, removing the heat to outer space. The account of the joint operation of both parts is necessary for the characteristics analysis.

The main portion of the neat inflow from the solar radiation and instruments is being removed toe the space by the passive cooling system. The heat transfer computation while efficiency estimation of the telescope passive cooling system represents a complicated problem, primarily, through the necessity to account for the complex geometry, the possibility of heat inflows along the system elements, and thermo-physical properties of the screens. This problem solution can be obtained only by the numerical methods with the visibility coefficients determination of individual elements between themselves and with the outer space.

The cooling system computation is being complicated by the following factors:

- complex geometry of the passive screens and cryoscreen, their position in space and relative to each other;

- large temperature gradients from 320 K to 4.5 K between the elements, leading to the presence of temperature deformations of the structural elements;

- thermo-optical coefficients the thermo-physical characteristics of the elements are strongly dependent on temperature as well;

- the presence of three different thermal control mechanisms, namely, passive protection employing cryogenic screens and cooling by cryogenic machines of various temperature levels.

All these reasons stipulate the need for the expanded thermal analysis of the cooling system with a mathematical model developing to determine the cooling efficiency and temperature fields of the system elements.

Thermal bonds identification is necessary for correct developing of the mathematical model and obtaining numerical characteristics of the cooling system. The structure under study consists of individual elements such as screen lobes, cryoscreen, reflector, frame, etc. Each element of the system possesses the thermal bonds: radiation, internal thermal conductivity due to the presence of temperature gradients within the element itself, thermal conductivity through the frame or thermal bridges with neighboring elements.

The temperature values were obtained for each structural element. However, within the limits of one screen they differ by no more than 1 K, since the model is centrally symmetric. This difference is associated with the calculations error.

The spacecraft thermal control system, ,with the “Millimetron” observatory positioned on it ensuring the required reflector operating temperature of 4.5 K,  was developed. These temperatures values allow estimating the passive cooling system efficiency. However, more accurate forecasts require the computations correction by increasing the number of finite elements, and considering thermal conductivity of the passive screens materials and complex structure of the thermal bridges.

Keywords:

spacecraft, thermal control system, reflector, helium temperatures, cryogenic screen, protective screens, conductive and radiative heat transfer, cryogenic installations, temperature fields, passive screens, passive cooling

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