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

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$499,000.00
Award Year:
1988
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Award Id:
5063
Agency Tracking Number:
5063
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
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
() -
Business Contact:
DR. JAVIER A. VALENZUELA
INVESTIGATOR
() -
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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