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MASCOT Thermal subsystem design

Celotti, Luca and Nadalini, Riccardo and Sołyga, Małgorzata and Baturkin, Volodymyr and Khairnasov, Sergey and Kravets, Vladimir (2014) MASCOT Thermal subsystem design. In: Proceedings of the 27th European Space Thermal Analysis Workshop, pp. 151-164. ESA/ESTEC. 27th European Space Thermal Analysis Workshop, 03.-04. Dez. 2013, Noordwijk, The Netherlands. ISSN 1022-6656

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Official URL: https://exchange.esa.int/thermal-workshop/attachments/workshop2013/index.html


MASCOT is a lander built by DLR, embarked on JAXA’s Hayabusa-2, a scientific mission to study the asteroid 162173 1999 JU3. It is a small lander, less than 300x300x200mm?, with onboard payloads (camera, magnetometer, radiometer and IR spectrometer), developed in collaboration by DLR and CNES. MASCOT lands on the asteroid surface, after being released by Hayabusa-2 from a very close position above the asteroid surface, and investigates the asteroid surface. The thermal design of the lander represents one of the main challenges in the whole project because of multiple constraints, depending on the mission phase, mass, power and free space available. MASCOT, notwithstanding its small size, is equipped with redundant heat-pipe system, MLI blanket, heaters. The thermal design of the lander has been chosen after a trade-off phase concerning the technology which could suit better the opposing requirements of the mission: low heat exchange between the lander and the exterior (including the main spacecraft) in cruise, possibility to transfer all the heat dissipated by the internal paylaods and electronic boards during operations on asteroid surface. After selecting the heat-pipe technology as baseline, a development phase was undertaken by the partners both in terms of manufacturing, testing, thermal characterization phase and analitical modelling in order to match the thermal requirements. Heaters are used to assure the survival of the most delicated parts of the lander during cold cruise phases: the battery cells (only primary battery on-board), the electronic boards and the main payload. Strict requirements are given by the main spacecraft in terms of maximum power available to heat the lander during cruise. MLI blankets are used where the available space allows it, e.g. to extra insulate the Ebox from the rest of the lander creating a „hot compartment" and between the lander and the main spacecraft to reduce the heat exchange with it during cruise below the given limits. The whole thermal concept in all its parts undertook a detailed modelling phase in parallel to an experimental phase in vacuum chamber to improve the model and to qualify the system.

Item URL in elib:https://elib.dlr.de/102992/
Document Type:Conference or Workshop Item (Speech)
Title:MASCOT Thermal subsystem design
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Celotti, Lucaluca.celotti (at) activespacetech.euUNSPECIFIED
Nadalini, RiccardoActive Space Technologies GmbH (Germany)UNSPECIFIED
Sołyga, MałgorzataActive Space Technologies GmbH (Germany)UNSPECIFIED
Baturkin, Volodymyrvolodymyr.baturkin (at) dlr.deUNSPECIFIED
Date:February 2014
Journal or Publication Title:Proceedings of the 27th European Space Thermal Analysis Workshop
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Page Range:pp. 151-164
Series Name:ESA-WPP-338
Keywords:Asteroid, Mission, Mascot, thermal control
Event Title:27th European Space Thermal Analysis Workshop
Event Location:Noordwijk, The Netherlands
Event Type:Workshop
Event Dates:03.-04. Dez. 2013
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Science and Exploration
DLR - Research area:Raumfahrt
DLR - Program:R EW - Erforschung des Weltraums
DLR - Research theme (Project):R - Project MASCOT (old)
Location: Bremen
Institutes and Institutions:Institute of Space Systems > Systemkonditionierung
Deposited By: Baturkin, Volodymyr
Deposited On:23 Feb 2016 12:27
Last Modified:10 May 2016 23:44

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