%0 Journal Article
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@archivingpolicy denypublisher denyfinaldraft24
%@issn 1359-4311
%@usergroup administrator
%@usergroup sergio
%3 development experomental.pdf
%@dissemination WEBSCI; PORTALCAPES.
%@secondarykey INPE-12923-PRE/8202
%A Riehl, Roger R.,
%A Dutra,  T.,
%T Development of an experimental loop heat pipe for application in future space missions
%B Applied Thermal Engineering
%D 2005
%V 25
%N 1
%P Applied Thermal Engineering 25 (1): 101-112 Jan 2005
%8 Jan.
%2 sid.inpe.br/iris@1916/2005/08.04.12.56.23
%4 sid.inpe.br/iris@1916/2005/08.04.12.56
%K loop heat pipe, thermal control, capillary evaporator, two-phase flow.
%X The application of loop heat pipes (LHPs) as two-phase thermal control devices for space missions has been considered and successfully used in many spacecraft. Therefore, issues related to design, miniaturization of such a device and use of hazardous working fluids such as ammonia are still a concern. In order to face such concerns, this paper presents the development of an experimental LHP that deals with miniaturization and the use of an alternative working fluid. An experimental LHP was built and tested with acetone as the working fluid, designed to manage up to 70 W and using a capillary evaporator with reduced active length. The experimental results showed good thermal management performance of the proposed LHP for the imposed limitations to its design and operation. The proposed LHP presented to be a reliable thermal management device for application in future space missions, especially when considering the use of a less hazardous working fluid and the particular geometric characteristics. (C) 2004 Elsevier Ltd. All rights reserved.
%@language English
%@copyholder SID/SCD
%@secondarytype PRE PI
%@area ETES
%@group DMC-INPE-MCT-BR
%@affiliation Instituto Nacional de Pesquisas Espaciais, Divisão de Mecânica Espacial e Controle (INPE-DMC),