Phase I Demonstration of a Heat Pump Loop Thermal Control System

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$69,999.00
Award Year:
2002
Program:
SBIR
Phase:
Phase I
Contract:
NAS9-01154
Award Id:
56316
Agency Tracking Number:
013355
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
200 Yellow Place, Rockledge, FL, 32955
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
Robert Scaringe
Research Mechanical Engineer
(321) 631-3550
rps@mainstream-engr.com
Business Contact:
Kathy McGraw-Davids
Comptroller
(321) 631-3550
mkd@mainstream-engr.com
Research Institute:
n/a
Abstract
Phase I will experimentally demonstrate the performance benefits of a Heat Pump Loop (HPL) Thermal Control Bus employing a unique working fluid which is not only non-toxic and environmentally-safe, but it will also survive the catalytic oxidizer on board spacecraft. Phase I will compare this unique system to pumped single-phase, pumped two-phase and heat pipe thermal control systems. Phase I will demonstrate a high-performance, environmentally-acceptable, manned-spacecraft-compatible heat pump loop thermal control system that exhibits the benefits of a two-phase pumped loop system, the thermal control and temperature lift of a heat pump augmented system, and the simplicity of a single-phase pumped loop system. Phase I will demonstrate that the HPL approach has the operational stability and flexibility to accommodate highly variable heat loads, variable radiator temperatures, and multiple cold-plate operating temperatures: That means increased thermal control flexibility for future spacecraft, and the possibility of a much more flexible and universal thermal bus. The Phase II effort would address coupling this technology with Mainstream's long life magnetic-bearing or oil-less compressor technology, coupling to compact high-temperature thermal storage devices, and fabrication of demonstration hardware for a Phase III flight test experiment.

* information listed above is at the time of submission.

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