Spacecraft thermal control single-phase fluid loop device based on novel shaftless pump

Abstract

The invention discloses a spacecraft thermal control single-phase fluid loop device based on a novel shaftless pump. The spacecraft thermal control single-phase fluid loop device comprises a liquid storage device, the novel shaftless pump, a first heat sink, a second heat sink and a fluid pipeline. A traditional driving pump is abandoned, and the novel shaftless pump capable of being used in regional series connection is adopted to drive a working medium to flow. The novel shaftless pump adopts the integrated design of a pump and a pipeline and the integrated design of a motor and the pump, so that the structure is more compact. The sealing problem of the pump in a fluid loop pipeline is solved, the on-way resistance of a loop is reduced, and meanwhile, the pump has the advantages of being capable of being rapidly integrated and high in adaptability. The device can be applied to heat transfer of small satellite spacecrafts and isothermal design of partial areas of the spacecrafts.

Description

technical field [0001] The invention relates to the field of fluid circuit devices, in particular to a spacecraft thermal control single-phase fluid circuit device based on a novel shaftless pump. Background technique [0002] In the face of complex thermal environments, spacecraft need to have certain thermal control methods, such thermal control methods include active thermal control technology and passive thermal control technology. As the complexity of space missions increases, passive thermal control methods, such as loop heat pipes and thermal insulation materials, often cannot meet the requirements of regional isothermalization or more heat transfer. At the same time, for some satellite thermal control systems that require higher precision, it is necessary to be able to adjust the heat transfer process. Therefore, active thermal control technology is particularly important. In recent years, as an important technical means of active thermal control of spacecraft, pum...

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Problems solved by technology

However, according to the index requirements of different satellite fluid circuits, it is necessary to select and design the drive pump and fluid circuit accordingly, which increases the research cost and task complexity

The design of traditional pumps also has problems of leakage and increased resistance along the pipeline

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