Development of a Mechanically Pumped Fluid Loop for 3 to 6 kW Payload Cooling

Benthem, R.C. van; Grave, W. de; Es, J. van; Elst, J.; Bleuler, R.; Tjiptahardja, Tisna

doi:10.4271/2009-01-2350

Cited by 9 publications

(6 citation statements)

References 1 publication

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“…In addition, considering the human and robotic exploration strategy, in the framework of the International Habitat (I-HAB) or Orion MPCV—European Service Module, an active thermal control system is needed and the centrifugal pump can be equipped with an additively manufactured impeller. Several studies [ 2 , 3 , 4 , 5 ] show that MPL systems were dedicated only to the International Space Station (ISS) and deep space missions, until the year 2000, when the European Space Agency (ESA) began developing an MPL system for large telecommunication platforms (currently operating on a Russian GEO satellite) and a mechanically pumped fluid loop (MPFL) for a 3–6 kW single-phase MPL system. The results and knowledge gathered laid the groundwork for a large (7–20 kW) two-phase MPL development for the thermal control of telecommunication satellites on the Neosat platform.…”

Section: Introductionmentioning

confidence: 99%

A Study on Using the Additive Manufacturing Process for the Development of a Closed Pump Impeller for Mechanically Pumped Fluid Loop Systems

et al. 2021

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The efficiency of a centrifugal pump for mechanical pump fluid loops, apart from the design, relies on the performance of the closed impeller which is linked to the manufacturing process in terms of dimensional accuracy and the surface quality. Therefore, the activities of this paper were focused on defining the manufacturing process of a closed impeller using the additive manufacturing technology for mechanically pumped fluid loop (MPFL) systems in space applications. Different building orientations were studied to fabricate three closed impellers using selective laser melting technology and were subjected to dimensional accuracy and surface quality evaluations in order to identify the optimal building orientation. The material used for the closed impeller is Inconel 625. The results showed that both geometrical stability and roughness were improved as the building orientation increased, however, the blade thickness presented small deviations, close to imposed values. Finishing processes for inaccessible areas presented significant results in terms of roughness, nevertheless, the process can be further improved. Abrasive flow machining (AFM) post-processing operations have been considered and the results show major improvements in surface quality. Thus, important steps were made towards the development of complex structural components, consequently increasing the technological readiness level of the additive manufacturing process for space applications.

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Section: Introductionmentioning

confidence: 99%

A Study on Using the Additive Manufacturing Process for the Development of a Closed Pump Impeller for Mechanically Pumped Fluid Loop Systems

et al. 2021

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“…The fluid loop is still a common option for thermal control systems intended for future crewed missions such as the deep-space gateway [13] and for uncrewed spacecraft with a large heat dissipation of several kilowatts [14]. Japan developed single-phase water (inner loop) and FC-72 (exposed loop) mechanically pumped loops for the thermal control system of the ISS's Japanese experiment module, Kibo [15,16].…”

Section: Nomenclaturementioning

confidence: 99%

Thermal Performance Evaluation of Space Radiator for Single-Phase Mechanically Pumped Fluid Loop

Iwata

Nakanoya

Nakamura

et al. 2022

Journal of Spacecraft and Rockets

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This paper presents the experimental and analytical results of a heat rejection system consisting of a single-phase mechanically pumped loop and a space radiator. It has been developed for future crewed exploration missions to provide a large amount of heat dissipation capability. The radiator consists of a honeycomb radiator, eight aluminum pipes inserted through the honeycomb core, and two aluminum manifolds joined at both ends of the eight pipes. A graphite sheet is attached to the back of the aluminum skin, facing deep space to improve the thermal diffusivity in the in-plane direction. Silverized Teflon® tapes are put on the surface of the skin on the deep-space side, and the surface of the opposite skin is covered with multilayer insulation. A gap between the radiator surface and the flow channel protects against micrometeoroids and orbital debris. A thermal vacuum test was conducted to evaluate the thermal performance of the radiator. The coolant was HFE7200, and its flow rate was varied from about 50 to 200 kg/h. More than 50 temperatures across the radiator surface were measured for each case. Thermal Desktop® and SINDA/FLUINT software were used to develop the thermal mathematical model, which was correlated with the test results and evaluated through thermal analysis. The fin efficiency of the radiator increased with the mass flow rate of the coolant, reaching 0.9 or higher.

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“…The autonomy of spacecraft necessitates the use of circulation systems in them that reproduce the processes that are natural for the existence of the biosphere on Earth. Centrifugal pumps are built into the circulation circuit of the thermal control system, which ensure the flow of the heat carrier [1,2].…”

Section: Introductionmentioning

confidence: 99%

Optical visualization as an effective tool for studying the flow structure in a small-sized centrifugal electric pump

Bobkov¹,

Krivenko²

2023

E3S Web of Conf.

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The article is devoted to the substantiation of the need for optical visualization of the structure of a 2-dimensional flow in small-sized centrifugal electric pumps of the spacecraft thermal control system. Reducing the size of the interblade channels of the pump impeller makes it impossible to use traditional methods of flow sensing due to disturbances introduced by the probes. Due to the lack of experimental data, in the study of flows in small pumps, a flow model developed for full-size centrifugal pumps is used. The most common of these are the Euler jet model or the two-zone jet-trail model. Studies by numerical methods based on these models cannot be verified for adequacy to real flows due to the lack of experimental data necessary to validate the results obtained. Under such conditions, the study of the flow structure by experimental methods, in particular, using optical visualization by the method of indicator washable coatings in the near-wall layer of the interblade channels of the impeller of pumps, becomes important. This article describes: 1) the technology of imaging; 2) structural elements of the flow, which are identified in the flow patterns in the near-wall layer; 3) results of visualization of the flow in the impellers of centrifugal pumps with a diameter of 41·10-3 m. New data are obtained on the structure of the flow under flow regimes in the non-self-similar zone of the Reynolds number in relative motion.

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Development of a Mechanically Pumped Fluid Loop for 3 to 6 kW Payload Cooling

Cited by 9 publications

References 1 publication

A Study on Using the Additive Manufacturing Process for the Development of a Closed Pump Impeller for Mechanically Pumped Fluid Loop Systems

A Study on Using the Additive Manufacturing Process for the Development of a Closed Pump Impeller for Mechanically Pumped Fluid Loop Systems

Thermal Performance Evaluation of Space Radiator for Single-Phase Mechanically Pumped Fluid Loop

Optical visualization as an effective tool for studying the flow structure in a small-sized centrifugal electric pump

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