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Title: Rotating bubble membrane radiator for space applications

Abstract

An advanced radiator concept for heat rejection in space is described which uses a two-phase working fluid to radiate waste heat. The development of new advanced materials and the large surface area per mass makes the Bubble Membrane Radiator an attractive alternative to both conventional heat pipes and liquid droplet radiators for mid-to-high-temperature applications. A system description, a discussion of design requirements, and a mass comparison with heat pipes and liquid droplet radiators is provided. To meet the increased demand for power, solar dynamic and nuclear power systems, which operate on a closed heat engine cycle or use direct conversion of thermal to electric power, are being investigated for their significant reduction in size and mass over comparable photovoltaic systems. This reduction in mass and size may translate into reduced initial and life cycle costs as well as improved orbital operations in the areas of stability, control, and maintenance. For any space-based activity, waste heat must ultimately be radiated to space. Spacecraft system studies by NASA and industry have shown that heat rejection radiator systems are a major weight and volume contributor to any power or thermal management system. The optimal design and development of future power or thermal managementmore » systems will require advanced heat rejection concepts utilizing new and innovative approaches to reduce overall system mass and size, while increasing system efficiency and thermodynamic performance. These advanced heat rejection systems will be required to withstand the detrimental effects of meteoroid and space debris impact, radiation, and ionizing atoms, in addition to addressing such pertinent mission requirements as reliability and maintainability, operation and control, system integration, and life cycle cost. 5 refs., 1 fig., 3 tabs.« less

Authors:
;
Publication Date:
Research Org.:
Pacific Northwest Lab., Richland, WA (USA)
OSTI Identifier:
5402679
Report Number(s):
PNL-SA-13674; CONF-860810-25
ON: DE86015059
DOE Contract Number:  
AC06-76RL01830
Resource Type:
Conference
Resource Relation:
Conference: Intersociety energy conversion engineering conference, San Diego, CA, USA, 25 Aug 1986
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; RADIATORS; COMPARATIVE EVALUATIONS; DESIGN; SYSTEMS ANALYSIS; WORKING FLUIDS; HEAT LOSSES; HEAT PIPES; MASS; METEOROIDS; SPACE VEHICLE COMPONENTS; WASTE HEAT; ENERGY; ENERGY LOSSES; FLUIDS; HEAT; HEAT EXCHANGERS; LOSSES; WASTES; 420200* - Engineering- Facilities, Equipment, & Techniques

Citation Formats

Webb, B J, and Antoniak, Z I. Rotating bubble membrane radiator for space applications. United States: N. p., 1986. Web.
Webb, B J, & Antoniak, Z I. Rotating bubble membrane radiator for space applications. United States.
Webb, B J, and Antoniak, Z I. 1986. "Rotating bubble membrane radiator for space applications". United States.
@article{osti_5402679,
title = {Rotating bubble membrane radiator for space applications},
author = {Webb, B J and Antoniak, Z I},
abstractNote = {An advanced radiator concept for heat rejection in space is described which uses a two-phase working fluid to radiate waste heat. The development of new advanced materials and the large surface area per mass makes the Bubble Membrane Radiator an attractive alternative to both conventional heat pipes and liquid droplet radiators for mid-to-high-temperature applications. A system description, a discussion of design requirements, and a mass comparison with heat pipes and liquid droplet radiators is provided. To meet the increased demand for power, solar dynamic and nuclear power systems, which operate on a closed heat engine cycle or use direct conversion of thermal to electric power, are being investigated for their significant reduction in size and mass over comparable photovoltaic systems. This reduction in mass and size may translate into reduced initial and life cycle costs as well as improved orbital operations in the areas of stability, control, and maintenance. For any space-based activity, waste heat must ultimately be radiated to space. Spacecraft system studies by NASA and industry have shown that heat rejection radiator systems are a major weight and volume contributor to any power or thermal management system. The optimal design and development of future power or thermal management systems will require advanced heat rejection concepts utilizing new and innovative approaches to reduce overall system mass and size, while increasing system efficiency and thermodynamic performance. These advanced heat rejection systems will be required to withstand the detrimental effects of meteoroid and space debris impact, radiation, and ionizing atoms, in addition to addressing such pertinent mission requirements as reliability and maintainability, operation and control, system integration, and life cycle cost. 5 refs., 1 fig., 3 tabs.},
doi = {},
url = {https://www.osti.gov/biblio/5402679}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Thu May 01 00:00:00 EDT 1986},
month = {Thu May 01 00:00:00 EDT 1986}
}

Conference:
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