Spacecraft two-phase fluid heat exchange loop thermal control system
A thermal control system and spacecraft technology, applied in indirect heat exchangers, lighting and heating equipment, etc., can solve the problems of single-stage systems that cannot meet demand, difficulty in starting, and heavy volume.
Active Publication Date: 2021-05-18
BEIHANG UNIV
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Problems solved by technology
[0004] At present, the capillary suction two-phase fluid circuit has the following limitations: 1) the single-stage system cannot meet the demand; 2) the driving force is insufficient, and it is difficult to start; 3) the life is short and the volume is heavy; 4) the performance and reliability are low
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[0028] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.
[0029] In describing the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", The orientation or positional relationship indicated by "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying the referred device or positional relationship. Elements must hav...
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The invention relates to a spacecraft two-phase fluid heat exchange loop thermal control system. The system comprises an evaporator-compensator which is of an integrated structure, wherein an evaporator and a compensator are sealed in a cylindrical metal shell, and a capillary core of the evaporator is provided with particle size holes distributed in a gradient mode and a plurality of tree-shaped micro-channels; one side of an air path in the evaporator-compensator communicates with one side of the condenser through a steam conveying pipeline, and the steam conveying pipeline is a hydrophilic pipeline; and the other side of the evaporator-compensator communicates with the other side of the condenser through a liquid conveying pipeline to form a closed loop, the liquid conveying pipeline is a hydrophobic pipeline, and a bypass channel used for vacuumizing or replenishing a liquid working medium is formed in the liquid conveying pipeline. The evaporator and the compensator are sealed into a whole, so that the structure is compact; and by using the capillary action formed by the particle size holes in gradient distribution and the micro-channel structure and the driving force formed by the step structure, the hydrophilic steam conveying pipeline accelerates condensation, the hydrophobic liquid conveying pipeline reduces resistance, and the requirements of a spacecraft platform for high efficiency, high reliability, compactness and the like of a thermal control system are met.
Description
technical field [0001] The invention relates to the technical field of heat dissipation of aerospace electronic devices, and more specifically relates to a thermal control system of a two-phase fluid heat exchange circuit of a spacecraft. Background technique [0002] The space environment where the spacecraft is located is extremely harsh, and the temperature ranges from minus one hundred degrees Celsius to minus one hundred degrees Celsius. If no thermal control measures are taken, the components and equipment on the spacecraft will be difficult to work and operate normally. Therefore, the thermal control system is one of the many important systems of the spacecraft. [0003] The aerospace thermal control system is a highly coupled and optimized system. Its structure is designed according to the heat flux density and layout of the satellite platform and load. The rapid development of globalization has put forward higher requirements for the thermal control efficiency of t...
Claims
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Login to View More IPC IPC(8): F28D15/04
CPCF28D15/046F28D15/0275
Inventor 郭伟张宏强薛俊良朱颖彭鹏
Owner BEIHANG UNIV