LOW FILM RESISTANCE CONDENSER FOR OPERATION IN A GRAVITY-FREE ENVIRONMENT

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: N/A
Agency Tracking Number: 5063
Amount: $499,000.00
Phase: Phase II
Program: SBIR
Awards Year: 1988
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
P.o. Box 71, Etna Rd, Hanover, NH, 03755
DUNS: 072021041
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 () -
Business Contact
 DR. JAVIER A. VALENZUELA
Title: INVESTIGATOR
Phone: () -
Research Institution
N/A
Abstract
TWO-PHASE THERMAL TRANSPORT LOOPS OFFER SIGNIFICANT WEIGHT AND PERFORMANCE ADVANTAGES OVER CONVENTIONAL SINGLE-PHASE SPACECRAFT THERMAL MANAGEMENT SYSTEMS. KEY COMPONENTS IN TWO-PHASE THERMAL MANAGEMENT SYSTEMS ARE THE CONDENSING AND EVAPORATING HEAT EXCHANGERS TO COUPLE THE LOADS TO THE TWO-PHASE THERMAL BUS, AND TO TRANSFER HEAT BETWEEN THE THERMAL BUS AND THE SPACECRAFT RADIATOR. THE MAIN REQUIREMENTS FOR THESE HEAT EXCHANGERS ARE THAT: 1) THEY CONTROL THE LOCATION OF MANAGE THE GAS AND LIQUID PHASES IN THE ABSENCE OF GRAVITY AND 2) THEY HAVE HIGH HEAT TRANSFER COEFFICIENTS; THAT IS, THEY OPERATE AT HIGH HEAT FLUXES WITHLOW OVERALL TEMPERATURE DIFFERENCES. A NOVEL CONDENSING HEAT EXCHANGER CONCEPT WHICH HAS THE POTENTIAL TO OPERATE AT HEAT TRANSFER COEFFICIENTS AN ORDER OF MAGNITUDE LARGER THAN IS POSSIBLE WITH CURRENT DESIGNS ISPROPOSED. PHASE I OF THIS PROJECT WILL ASSESS THE FEASIBILITY OF THE PROPOSED HEAT EXCHANGER BY PERFORMING A PROOF-OF-CONCEPT EXPERIMENT AND DEVELOPING SCOPING ANALYSES TO ESTIMATE ITS EXPECTED RANGE OF PERFORMANCE. IF PROVEN FEASIBLE, A PROTOTYPE HEAT EXCHANGER WILL BE BUILT AND TESTED IN PHASE II.

* Information listed above is at the time of submission. *

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