The use of heat pipes and loop heat pipes (LHPs) as thermal control devices in satellites and other spacecrafts have increased considerably during the last decades. Due to the need of a crescent demand on heat dissipation, more of these devices have been used in low orbit and geo‐stationary satellites to promote the adequate thermal control for the instrumentation and equipments aboard. Even though each design is dedicated to a specific application, heat pipes and LHPs have to go through acceptance tests prior to be integrated in the satellite’s honeycomb panels (in case of most heat pipes applications) and instrumentation (in case of LHPs thermal control). In order to give a guideline for the required acceptance tests that heat pipes and LHPs have to be submitted, this paper presents the constraints that need to be considered while performing those tests. In all cases, the acceptance tests for both heat pipes and LHPs are related to the most important conditions to verify their proper operation before integrating them on their designed application in a satellite. Such acceptance tests are important to correctly evaluate these thermal control devices and avoid malfunctions while qualifying the entire satellite.


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    Title :

    Heat Pipes and Loop Heat Pipes Acceptance Tests for Satellites Applications


    Contributors:

    Conference:

    SPACE, PROPULSION & ENERGY SCIENCES INTERNATIONAL FORUM: SPESIF‐2009 ; 2009 ; Huntsville (Alabama)


    Published in:

    AIP Conference Proceedings ; 1103 , 1 ; 82-90


    Publication date :

    2009-03-16


    Size :

    9 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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