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Record 1 of 48236
Miniature Heat Transport System for Nanosatellite Technology
Author and Affiliation:
Douglas, Donya M,(NASA Goddard Space Flight Center, Greenbelt, MD United States)
Abstract: The scientific understanding of key physical processes between the Sun and the Earth require simultaneous measurements from many vantage points in space. Nano-satellite technologies will enable a class of constellation missions for the NASA Space Science Sun-Earth Connections. This recent emphasis on the implementation of smaller satellites leads to a requirement for development of smaller subsystems in several areas. Key technologies under development include: advanced miniaturized chemical propulsion; miniaturized sensors; highly integrated, compact electronics; autonomous onboard and ground operations; miniatures low power tracking techniques for orbit determination; onboard RF communications capable of transmitting data to the ground from far distances; lightweight efficient solar array panels; lightweight, high output battery cells; lightweight yet strong composite materials for the nano-spacecraft and deployer-ship structures. These newer smaller systems may have higher power densities and higher thermal transport requirements than seen on previous small satellites. Furthermore, the small satellites may also have a requirement to maintain thermal control through extended earth shadows, possibly up to 8 hours long. Older thermal control technology, such as heaters, thermostats, and heat pipes, may not be sufficient to meet the requirements of these new systems. Conversely, a miniature two-phase heat transport system (Mini-HTS) such as a Capillary Pumped Loop (CPL) or Loop Heat Pipe (LBP) is a viable alternative. A Mini-HTS can provide fine temperature control, thermal diode action, and a highly efficient means of heat transfer. The Mini-HTS would have power capabilities in the range of tens of watts or less and provide thermal control over typical spacecraft ranges. The Mini-HTS would allow the internal portion of the spacecraft to be thermally isolated from the external radiator, thus protecting the internal components from extreme cold temperatures during an eclipse. The Mini-HTS would transport the beat from these components to a radiator during their operational modes, and it would be shutdown during non-operational or eclipse modes. Shutdown of the Mini-HTS would be accomplished with small heaters and has been successfully demonstrated on numerous occasions, both in the lab and on flight experiments. Efforts are now underway to miniaturize two-phase heat transport systems for the Nanosatellite project, with potential application to other small satellite programs. 'ne goal of this project is to design, build, and test miniature heat transport systems (MHTS) that would demonstrate the feasibility of a small Capillary Pumped Loop (CPL) or Loop Heat Pipe (LBP).
Publication Date: Jan 01, 1999
Document ID:
19990067284
(Acquired Sep 17, 1999)
Subject Category: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Document Type: Reprint
Meeting Information: Two Phase 1999 Workshop; 17-19 May 1999; Greenbelt, MD; United States
Financial Sponsor: NASA Goddard Space Flight Center; Greenbelt, MD United States
Organization Source: NASA Goddard Space Flight Center; Greenbelt, MD United States
Description: In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: HEAT TRANSFER; COMMUNICATION EQUIPMENT; GROUND OPERATIONAL SUPPORT SYSTEM; HEAT PIPES; MINIATURIZATION; NANOSATELLITES; AUTONOMY; CHEMICAL PROPULSION; CONSTELLATIONS; DEPLOYMENT; ELECTRIC BATTERIES; HEAT EXCHANGERS; LOW TEMPERATURE; ORBIT CALCULATION; SUN; TEMPERATURE CONTROL
Availability Source: Other Sources
Availability Notes: Abstract Only
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