Research Papers

Defining a Discretized Space Suit Surface Radiator With Variable Emissivity Properties

[+] Author and Article Information
Christopher J. Massina

Aerospace Engineering Sciences,
University of Colorado Boulder,
429 UCB,
Boulder, CO 80309
e-mail: christopher.massina@colorado.edu

David M. Klaus

Aerospace Engineering Sciences,
University of Colorado Boulder,
429 UCB,
Boulder, CO 80309
e-mail: klaus@colorado.edu

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received February 21, 2015; final manuscript received July 4, 2015; published online August 12, 2015. Assoc. Editor: Steve Cai.

J. Thermal Sci. Eng. Appl 7(4), 041014 (Aug 12, 2015) (9 pages) Paper No: TSEA-15-1048; doi: 10.1115/1.4031132 History: Received February 21, 2015

Heat rejection for space suit thermal control is typically achieved by sublimating water ice to vacuum. Converting the majority of a space suit's surface area into a radiator may offer an alternative means of heat rejection, thus reducing the undesirable loss of water mass to space. In this work, variable infrared (IR) emissivity electrochromic materials are considered and analyzed as a mechanism to actively modulate radiative heat rejection in the proposed full suit radiator architecture. A simplified suit geometry and lunar pole thermal environment is used to provide a first-order estimate of electrochromic performance requirements, including number of individually controllable pixels and the emissivity variation that they must be able to achieve to enable this application. In addition to several implementation considerations, two fundamental integration architecture options are presented—constant temperature and constant heat flux. With constant temperature integration, up to 48 individual pixels with an achievable emissivity range of 0.169–0.495 could be used to reject a metabolic load range of 100 W–500 W. Alternatively, with constant heat flux integration, approximately 400 pixels with an achievable emissivity range of 0.122–0.967 are required to reject the same load range in an identical external environment. Overall, the use of variable emissivity electrochromics in this capacity is shown to offer a potentially feasible solution to approach zero consumable loss thermal control in space suits.

Copyright © 2015 by ASME
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Griffin, B. N. , Spampinato, P. , and Wilde, R. C. , 1999, “ Extravehicular Activity (EVA) Systems,” Human Spaceflight: Mission Analysis and Design, W. J. Larson and L. K. Pranke , eds., McGraw-Hill, New York.
Harris, G. L. , 2001, The Origins and Technology of the Advanced Extravehicular Space Suit (AAS History Series), Vol. 24, Univelt, San Diego, CA.
Farrington, R. , Rugh, J. , Bharathan, D. , Paul, H. , Bue, G. , and Trevino, L. , 2005, “ Using a Sweating Manikin, Controlled by a Human Physiological Model, to Evaluate Liquid Cooling Garments,” SAE Paper No. 2005-01-2971.
Campbell, A. B. , French, J. D. , Nair, S. S. , Miles, J. B. , and Lin, C. H. , 2000, “ Thermal Analysis and Design of an Advanced Space Suit,” J. Thermophys. Heat Transfer, 14(1), pp. 151–160. [CrossRef]
Ochoa, D. A. , Mirinda, B. , Conger, B. , and Trevino, L. , 2006, “ Lunar EVA Thermal Environment Challenges,” SAE Paper No. 2006-01-2231.
Race, M. S. , Criswell, M. E. , and Rummel, J. D. , 2003, “ Planetary Protection Issues in the Human Exploration of Mars,” SAE Paper No. 2003-01-2523.
Hedgeland, R. J. , Hansen, P. A. , and Hughes, D. W. , 1994, “ Integrated Approach for Contamination Control and Verification for the Hubble Space Telescope First Servicing Mission,” Proc. SPIE 2261, pp. 10–21.
Nabity, J. A. , Mason, G. R. , Copeland, R. J. , and Trevino, L. A. , 2008, “ A Freezable Heat Exchanger for Space Suit Radiator Systems,” SAE Paper No. 2008-01-2111.
Richardson, D. L. , 1965, “ Study and Development of Materials and Techniques for Passive Thermal Control of Flexible Extravehicular Space Garments,” Report No. AMRL-TR-65-156.
Hodgson, E. W. , Bender, A. , Goldfarb, J. , Hansen, H. , Quinn, G. , Sribnik, F. , and Thibaud-Erkey, C. , 2004, “ A Chameleon Suit to Liberate Human Exploration of Space Environments,” NASA Institute for Advanced Concepts, Contract No. 07600-082.
Metts, J. G. , Nabity, J. A. , and Klaus, D. M. , 2011, “ Theoretical Performance Analysis of Electrochromic Radiators for Space Suit Thermal Control,” Adv. Space Res., 47(7), pp. 1256–1264. [CrossRef]
Metts, J. G. , and Klaus, D. M. , 2012, “ First-Order Feasibility Analysis of a Space Suit Radiator Concept Based on Estimation of Water Mass Sublimation Using Apollo Mission Data,” Adv. Space Res., 49(1), pp. 204–212. [CrossRef]
Metts, J. G. , and Klaus, D. M. , 2009, “ Conceptual Analysis of Electrochromic Radiators for Space Suits,” SAE Paper No. 2009-01-2570.
Chandrasekhar, P. , Zay, B. J. , Birur, G. C. , Rawal, S. , Pierson, E. A. , Kauder, L. , and Swanson, T. , 2002, “ Large, Switchable Electrochromism in the Visible Through Far-Infrared in Conducting Polymer Devices,” Adv. Funct. Mater., 12(2), pp. 95–103. [CrossRef]
Kislov, N. , Groger, H. , and Ponnappan, R. , 2003, “ All-Solid-State Electrochromic Variable Emittance Coatings for Thermal Management in Space,” Space Technology and Applications International Forum, American Institute of Physics, Albuquerque, NM, pp. 172–179.
Ashwin-Ushas Corp., 2014, “ Variable Emittance Electrochromic Materials for Spacecraft Thermal Control: Our Unique, Patented Technology in a Nutshell,” http://www.ashwin-ushas.com/EleHome/SpaceThermal/spacethermal.html (last accessed Oct. 7, 2014).
Hager, P. B. , Walter, U. , Massina, C. J. , and Klaus, D. M. , 2015, “ Characterizing a Transient Heat Flux Envelope for Lunar Surface Space Suit Thermal Control Applications,” J. Spacecr. Rockets, (to be published).
NASA HIDH, 2010, Human Integration Design Handbook, National Aeronautics and Space Administration, Washington, DC, Report No. NASA/SP-2010-3407, Rev. Baseline.-oe23.
Sompayrac, R. , Conger, B. , and Trevino, L. , 2009, “ Lunar Portable Life Support System Heat Rejection Study,” SAE Paper No. 2009-01-2408.
Izenson, M. G. , Chen, W. , Phillips, S. , and Bue, G. , 2011, “ Nonventing Thermal and Humidity Control for EVA Suits,” AIAA Paper No. 2011-5260.
Gilmore, D. G. , 2002, Spacecraft Thermal Control Handbook–Volume I: Fundamental Technologies, The Aerospace Press, El Segundo, CA.
Massina, C. J. , Klaus, D. M. , and Sheth, R. B. , 2014, “ Evaluation of Heat Transfer Strategies to Incorporate a Full Suit Radiator for Thermal Control in Space Suits,” 44th International Conference on Environmental Systems, Tucson, AZ, Paper No. ICES-2014-089.
Hager, P. B. , 2013, “ Dynamic Thermal Modeling for Moving Objects on the Moon,” Ph.D. thesis, Technische Universität München, Munich.
Granqvist, C. G. , 1995, Handbook of Inorganic Electrochromic Materials, Elsevier, Amsterdam, Chap. 1.
Incropera, F. P. , DeWitt, D. P. , Bergman, T. L. , and Lavine, A. S. , 2007, Fundamentals of Heat and Mass Transfer, 6th ed., Wiley, Hoboken, NJ, Chaps. 12 and 13.
Siegel, R. , and Howell, J. , 2002, Thermal Radiation Heat Transfer, 4th ed., Taylor & Francis, New York.
Hale, J. S. , and Woollam, J. A. , 1999, “ Prospects for IR Emissivity Control Using Electrochromic Structures,” Thin Solid Films, 339(1–2), pp. 174–180. [CrossRef]
Demiryont, H. , and Moorehead, D. , 2009, “ Electrochromic Emissivity Modulator for Spacecraft Thermal Management,” Sol. Energy Mater. Sol. Cells, 93(12), pp. 2075–2078. [CrossRef]
Bannon, E. T. , Bower, C. E. , Sheth, R. , Stephan, R. , Chandrasekhar, P. , and Zay, B. , 2010, “ Electrochromic Radiator Coupon Level Testing and Full Scale Thermal Math Modeling for Use on Altair Lunar Lander,” AIAA Paper No. 2010-6110.
Chandrasekhar, P. , Zay, B. J. , Lawrence, D. , Caldwell, E. , Sheth, R. , Stephan, R. , and Cornwell, J. , 2014, “ Variable-Emittance Infrared Electrochromic Skins Combining Unique Conducting Polymers, Ionic Liquid Electrolytes, Microporous Polymer Membranes, and Semiconductor/Polymer Coatings, for Spacecraft Thermal Control,” J. Appl. Polym. Sci., 131(19), p. 40850. [CrossRef]
Havenith, G. , 1999, “ Heat Balance When Wearing Protective Clothing,” Ann. Occup. Hyg., 43(5), pp. 289–296. [CrossRef] [PubMed]
Buckey, J. C. , 2006, Space Physiology, Oxford University, Oxford, UK.
Pitts, B. , Brensinger, C. , Saleh, J. , Carr, C. , Schmidt, P. , and Newman, D. , 2001, “ Astronaut Bio-Suit for Exploration Class Missions,” NIAC Phase I Report, http://www.4frontiers.us/dev/assets/BioSuit-NIACPhaseIReport.pdf
Tepper, E. H. , Trevino, L. A. , and Anderson, J. E. , 1991, “ Results of Shuttle EMU Thermal Vacuum Tests Incorporating an Infrared Imaging Camera Data Acquisition System,” SAE Paper No. 911388.
Guibert, A. , and Taylor, C. L. , 1952, “ Radiation Area of the Human Body,” J. Appl. Physiol., 5(1), pp. 24–37, http://jap.physiology.org/content/5/1/24. [PubMed]
Chambers, A. B. , 1970, “ Controlling Thermal Comfort in the EVA Space Suit,” ASHRAE, 12, pp. 33–38.
Hager, P. B. , Klaus, D. M. , and Walter, U. , 2014, “ Characterizing Transient Thermal Interactions Between Lunar Regolith and Surface Spacecraft,” Planet. Space Sci., 92, pp. 101–116. [CrossRef]


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Fig. 1

Representative response to state variation and continuous thermal state averaging heat dissipation schemes

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Fig. 5

Example of effective net emissivity values achieved by high–low state mixing

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Fig. 4

Example of intermediate emissivity settings achieved with a variable potential source

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Fig. 3

Mechanical counter pressure suit concept and constant flux concept. Space suit image credit: Professor Dava Newman, MIT. (Used with permission–Illustration: Cam Brensinger.) Integration scheme modified from Ref. [13].

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Fig. 2

The EMU and one constant temperature radiator integration concept. (Space suit image credit: NASA). Integration scheme modified from Ref. [13].

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Fig. 7

Cylinder area approximation's interactions with the lunar pole environment. A, B, C, and D correspond to β angles at 90 deg increments starting with A =  0 deg

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Fig. 6

Space suit radiator surface area scaled to a cylinder approximation

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Fig. 9

Radiative power distributions with variation in emissivity and radiator temperature

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Fig. 8

Radiative power distributions across suit segments, 293.72 K (69.02 °F)

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Fig. 13

Allowable total emissivity variations for thermal comfort

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Fig. 10

Suit temperature requirements for constant flux segment dissipation, 300 W

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Fig. 11

Emissivity setting requirements for constant flux at a lunar pole at 300 W of constant dissipation

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Fig. 12

Emissivity setting requirements for constant flux in lunar pole environment



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