Spacecraft Two-Phase Thermal Control System Simulation

1997 ◽  
Author(s):  
Vladimir V. Malozemov ◽  
Natalia S. Kudriavtseva
Keyword(s):  
Control System ◽  
System Simulation ◽  
Thermal Control ◽  
Two Phase ◽  
Thermal Control System

Состояние разработок двухфазных систем терморегулирования космических аппаратов

2021 ◽  
pp. 36-51
Author(s):  
Рустем Юсуфович Турна ◽  
Артем Михайлович Годунов
Keyword(s):  
Heat Transfer ◽  
Control System ◽  
Power Consumption ◽  
High Power ◽  
Single Phase ◽  
Thermal Control ◽  
Two Phase ◽  
Thermal Control System ◽  
Intensification Of Heat Exchange ◽  
Large Heat

The progress of space technology is leading to more and more energy-equipped spacecraft. The International Space Station already has the capacity of solar panels of more than 100 kW. Autonomous spacecrafts and satellites (including stationary ones) have the capacity of power units of kW, in the nearest future - more than 10 kW. Forced heat transfer using single-phase liquid coolants is still considered as the main method of thermal control on high-power spacecraft (SC). Single-phase mechanically pumped fluid loop is a fully proven means of thermal control of spacecraft with a moderate heat load. A significant disadvantage of such systems is that the coolant temperature varies significantly within the loop. The temperature difference can be reduced by increasing the coolant flow rate, but for this, it is necessary to increase the pump capacity, which inevitably leads to an increase in power consumption, pipeline diameters, and weight of the system as a whole. In the case of spacecraft with high power capacity (more than 5-10 kW) and large heat transfer distances (10 m and more), a two-phase mechanically pumped fluid loop for thermal control is more preferable in terms of weight, the accuracy of thermoregulation, power consumption (and other parameters). The use of a two-phase loop (2PMPL) as a spacecraft thermal control system allows to reduce significantly mass and power consumption for own needs in comparison with a single-phase thermal control system (TCS). The effect is achieved due to the accumulation of transferred heat in the form of latent heat of vaporization and intensification of heat exchange at boiling and condensation of coolant. The article provides a critical review of published works on 2PMPL for spacecraft with high power (more than 5...10 kW) and a large heat transfer distance (more than 10...100 meters) from 1980 up to nowadays. As a result, a list of the main problems on the way of practical implementation of two-phase loops is formed.

Dynamic Characteristics of Two-Phase Thermal Control System for Spacecraft

1992 ◽  
Author(s):  
Vladimir V. Malozemov ◽  
Natalia S. Kudriavtseva ◽  
Victor A. Antonov ◽  
Oleg V. Zagar ◽  
Nikolai N. Chernobaev
Keyword(s):  
Control System ◽  
Dynamic Characteristics ◽  
Thermal Control ◽  
Two Phase ◽  
Thermal Control System

scholarly journals An Experiment of the Dynamic Characteristics of a Two-Phase Flow Thermal Control System.

2003 ◽  
Vol 69 (677) ◽  
pp. 100-106 ◽  
Author(s):  
Terushige FUJII ◽  
Katsumi SUGIMOTO ◽  
Eiji NISHIDA ◽  
Masanobu WADA ◽  
Shinichi TOYAMA ◽  
...  
Keyword(s):  
Control System ◽  
Dynamic Characteristics ◽  
Two Phase Flow ◽  
Thermal Control ◽  
Phase Flow ◽  
Two Phase ◽  
Thermal Control System

Dynamic Characteristics of a Two-phase Flow Thermal Control System

2002 ◽  
Vol 2002.77 (0) ◽  
pp. _11-19_-_11-20_
Author(s):  
E. NISHIDA ◽  
T. FUJII ◽  
H. ASANO ◽  
K. SUGIMOTO ◽  
M. WADA
Keyword(s):  
Control System ◽  
Dynamic Characteristics ◽  
Two Phase Flow ◽  
Thermal Control ◽  
Phase Flow ◽  
Two Phase ◽  
Thermal Control System

Thermal Performance of a Miniature Loop Heat Pipe for Spacecraft Thermal Control System

2007 ◽  
Author(s):  
Hiroki Nagai ◽  
Hosei Nagano ◽  
Fuyuko Fukuyoshi ◽  
Hiroyuki Ogawa
Keyword(s):  
Control System ◽  
Thermal Performance ◽  
High Power ◽  
Thermal Control ◽  
Working Fluid ◽  
Two Phase ◽  
Steady State Condition ◽  
Porous Wick ◽  
Thermal Control System ◽  
Spacecraft Thermal Control

The Loop Heat Pipes (LHPs) are robust, self-starting and a passive two-phase thermal control system that uses the latent heat of vaporization of an internal working fluid to transfer heat from an evaporator (the heat source) to a condenser (the heat sink). The circulation of the working fluid is accomplished by capillary pressure gradients in a fine porous wick with very small pores. LHPs are rapidly gaining acceptance in the aerospace community and several terrestrial applications are emerging as well. In the present study, a miniature LHP is investigated the thermal performance for spacecraft thermal control system. Tests will be conducted including start-up, low power, power ramp up, high power, rapid power change, and rapid sink temperature change. Finally, we want to demonstrate the potential of LHP to become the next-generation heat transfer device to cool terrestrial devices such as advanced electronic which have high power dissipations. First of all, this paper presents the influence of the gravitational forces on the LHP performance. The present tests performed under steady state condition with three different orientations (horizontal, gravity-assisted, anti-gravity).

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