Development of the variable emittance thermal suite for the space technology 5 microsatellite

Details Development of the variable emittance thermal suite for the space technology 5 microsatellite Development of the variable emittance thermal suite for the space technology 5 microsatellite

Jan 2002

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002aipc..608..204d&link_type=abstract

SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM- STAIF 2002. Conference on Thermophyiscs in Microgravity; Conference on In

Statistics

Applications

Thermal Instruments And Apparatus, Spaceborne And Space Research Instruments, Apparatus, And Components

Scientific paper

The advent of very small satellites, such as nano and microsatellites, logically leads to a requirement for smaller thermal control subsystems. In addition, the thermal control needs of the smaller spacecraft/instrument may well be different from more traditional situations. For example, power for traditional heaters may be very limited or unavailable, mass allocations may be severely limited, and fleets of nano/microsatellites will require a generic thermal design as the cost of unique designs will be prohibitive. Some applications may require significantly increased power levels while others may require extremely low heat loss for extended periods. Small spacecraft will have low thermal capacitance thus subjecting them to large temperature swings when either the heat generation rate changes or the thermal sink temperature changes. This situation, combined with the need for tighter temperature control, will present a challenging situation during transient operation. The use of ``off-the-shelf'' commercial spacecraft buses for science instruments will also present challenges. Older thermal technology, such as heaters, thermostats, and heat pipes, will almost certainly not be sufficient to meet the requirements of these new spacecraft/instruments. They are generally too heavy, not scalable to very small sizes, and may consume inordinate amounts of power. Hence there is a strong driver to develop new technology to meet these emerging needs. Variable emittance coatings offer an exciting alternative to traditional control methodologies and are one of the technologies that will be flown on Space Technology 5, a mission of three microsatellites designed to validate ``enabling'' technologies. Several studies have identified variable emittance coatings as applicable to a wide range of spacecraft, and to potentially offer substantial savings in mass and/or power over traditional approaches. This paper discusses the development of the variable emittance thermal suite for ST-5. More specifically, it provides a description of and the infusion and validation plans for the variable emittance coatings. .

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