Computer Science – Performance
Scientific paper
Apr 1994
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994fmai.reptq....g&link_type=abstract
Final Report Foster-Miller Associates, Inc., Waltham, MA.
Computer Science
Performance
Compressors, Heat Exchangers, Heat Pumps, High Temperature, Refrigerants, Thermodynamic Cycles, Heat Radiators, Heat Sources, Lunar Bases, Selection, Temperature Control, Thermal Environments
Scientific paper
This report describes the Phase 1 process and analysis used to select a refrigerant and thermodynamic cycle as the basis of a vapor compression heat pump requiring a high temperature lift, then to perform a preliminary design to implement the selected concept, including major component selection. Use of a vapor compression heat pump versus other types was based on prior work performed for the Electric Power Research Institute. A high lift heat pump is needed to enable a thermal control system to remove heat down to 275K from a habitable volume when the external thermal environment is severe. For example, a long-term lunar base habitat will reject heat from a space radiator to a 325K environment. The first step in the selection process was to perform an optimization trade study, quantifying the effect of radiator operating temperature and heat pump efficiency on total system mass; then, select the radiator operating temperature corresponding to the lowest system mass. Total system mass included radiators, all heat pump components and the power supply system. The study showed that lunar night operation, with no temperature lift, dictated the radiator size. To operate otherwise would require a high mass penalty to store power. With the defined radiation surface, and heat pump performances assumed to be from 40 percent to 60 percent of the Carnot ideal, the optimum heat rejection temperature ranged from 387K to 377K, as a function of heat pump performance. Refrigerant and thermodynamic cycles were then selected to best meet the previously determined design conditions. The system was then adapted as a ground-based prototype lifting temperature to 360K (versus 385K for flight unit) and using readily available commercial-grade components. Over 40 refrigerants, separated into wet and dry compression behavioral types, were considered in the selection process. Refrigerants were initially screened for acceptable critical temperature. The acceptable refrigerants were analyzed in ideal single and two-stage thermodynamic cycles. Top candidates were analyzed assuming realistic component limits and system pressure drops, and were evaluated for other considerations such as safety, environmental impact and commercial availability. A maximum coefficient of performance (COP) of 56 percent of the Carnot ideal was achievable for a three-stage CFC-11 cycle operating under the flight conditions above. The program was completed by defining a control scheme and by researching and selecting the major components, compressor and heat exchangers, that could be used to implement the thermodynamic cycle selected. Special attention was paid to using similar technologies for the SIRF and flight heat pumps resulting in the commercially available equivalent of the flight unit.
Goldman Jeffrey H.
Harvey Alex
Lovell T.
Walker David H.
No associations
LandOfFree
Lunar base heat pump, phase 1 draft does not yet have a rating. At this time, there are no reviews or comments for this scientific paper.
If you have personal experience with Lunar base heat pump, phase 1 draft, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Lunar base heat pump, phase 1 draft will most certainly appreciate the feedback.
Profile ID: LFWR-SCP-O-1256575