Development Status of the Mechanically Pumped Two-Phase CO2 Cooling Loop for the AMS-2 TTCS

Delil, A.A.M.; Woering, A.A.; Verlaat, B.

doi:10.1063/1.1541281

Cited by 6 publications

(1 citation statement)

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“…Each ASTS Thermal Block at the end of the copper strip is connected to an evaporator block of the mechanically pumped TTCS (Tracker Thermal Control System) by two copper braids (ASTS Thermal Connector). The AMS-02 TTCS is a two-phase CO 2 based heat transport system [8] developed at NLR and NIKHEF for the Si Tracker. ASTT controls only the temperatures of the CCD and the electronics, therefore conductive interfaces between ASTT and composite structure are protected by insulating material.…”

Section: Ast Thermal Control System (Astt)mentioning

confidence: 99%

The AMS Star Tracker Thermal Qualification Overview

Cascioli¹,

Borsini²,

Gargiulo³

et al. 2007

SAE Technical Paper Series

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Four different thermal-vacuum tests were performed on AMICA Star Tracker (AST) in the period March-July 2006 in the space simulator of the SERMS laboratory in Terni-Italy. Each of these tests was designed to verify different AST camera design features. The Thermal Balance test was conceived to validate the thermo-elastic model of the instrument and the active and passive thermal control subsystems. The Thermal Vacuum Cycling test was conceived to validate the AST electronics operative and survival temperature limits under vacuum conditions. The worst hot and cold operative and survival limits of the lens and filters in the AST optical system were assessed by means of the "Sun in the lens" and Lens Cold tests.

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Section: Ast Thermal Control System (Astt)mentioning

confidence: 99%

The AMS Star Tracker Thermal Qualification Overview

Cascioli¹,

Borsini²,

Gargiulo³

et al. 2007

SAE Technical Paper Series

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Study on the flow boiling characteristics of novel pin fin heat sinks in a two-phase mechanically pumped cooling loop

Wang,

Qi,

et al. 2024

Case Studies in Thermal Engineering

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Retrospective Review of a Two-Phase Mechanically Pumped Loop for Spacecraft Thermal Control Systems

Gorbenko¹,

Gakal²,

Turna³

et al. 2021

J. of Mech. Eng.

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The main issues associated with the development of two-phase mechanically pumped loops (2-MPL) for thermal control systems of spacecraft with large heat dissipation were formulated back in the early 80s. They have undeniable advantages over single-phase loops with mechanical pumping and two-phase capillary pumped loops at power more than 6 kW and heat transfer distance more than 10 meters. Intensive research and development of such systems started in the USA together with European, Canadian and Japanese specialists due to plans to build new high-power spacecraft and the Space Station Freedom project. In the 90's, S. P. Korolev Rocket and Space Corporation Energia (Russia) was developing a 2-MPL for the Russian segment of the International Space Station with the capacity of 20...30 kW. For this purpose, leading research organizations of the former Soviet Union were involved. In the last two decades, interest in two-phase heat transfer loops has significantly increased because of high-power stationary communications satellites and autonomous spacecraft for Lunar and Martian missions. The paper presents a retrospective review of worldwide developments of 2-MPLs for thermal control systems of spacecraft with large heat dissipation from the early 80's to the present. The participation of scientists and engineers of the Ukrainian National Aerospace University "KhAI" and the Center of Technical Physics is considered. The main directions of research, development results, and scientific and technical problems on the way to the practical implementation of such system are considered. Despite a large amount of research and development work done, there were no practically implemented projects of spacecraft with the high-power thermal control system until recent days. The first powerful stationary satellite with the 2-MPL was SES-17 satellite on the NEOSAT platform by Thales Alenia Space - France. The satellite was successfully launched into space on October 24, 2021 by onboard Ariane 5 launcher operated by Arianespace from the Europe’s Spaceport in Kourou, French Guiana.

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Development Status of the Mechanically Pumped Two-Phase CO2 Cooling Loop for the AMS-2 TTCS

Cited by 6 publications

References 0 publications

The AMS Star Tracker Thermal Qualification Overview

The AMS Star Tracker Thermal Qualification Overview

Study on the flow boiling characteristics of novel pin fin heat sinks in a two-phase mechanically pumped cooling loop

Retrospective Review of a Two-Phase Mechanically Pumped Loop for Spacecraft Thermal Control Systems

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