NASA SBIR 2016 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 16-2 S3.07-7413
PHASE 1 CONTRACT NUMBER: NNX16CP51P
SUBTOPIC TITLE: Thermal Control Systems
PROPOSAL TITLE: An Efficient, Reliable, Vibration-Free Refrigerant Pump for Space Applications

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Creare, LLC
16 Great Hollow Road
Hanover, NH 03755 - 3116
(603) 643-3800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Weibo Chen
wbc@creare.com
16 Great Hollow Road
Hanover, NH 03755 - 3116
(603) 643-3800 Extension :2425

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Kline-Schoder
contractsmgr@creare.com
16 Great Hollow Road
Hanover, NH 03755 - 3116
(603) 643-3800 Extension :2487

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

Technology Available (TAV) Subtopics
Thermal Control Systems is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
NASA's future remote sensing science missions require advanced thermal management technologies to maintain multiple instruments at very stable temperatures and utilize waste heat to keep other critical subsystems above minimum operational temperatures. Two-phase pumped loops are an ideal solution for these applications. A critical need for these pumped loops is a refrigerant pump that reliably circulates very slightly subcooled liquid refrigerant in the loop. Creare proposes to develop a reliable, vibration-free pump that has innovative features to prevent cavitation in the pumping chamber and in the hydrodynamic fluid bearings, enhancing the overall pumped loop reliability. The development of the refrigerant pump is built on Creare's proven pump technologies for space applications. In Phase I, we designed and built a proof-of-concept refrigerant pump and demonstrated its ability to reliably achieve the target flow rate and pressure rise, with a minimum required Net Positive Suction Head (NPSH) less than 0.5 psi. In Phase II, we will optimize the pump rotor, bearing and motor designs; assemble a pump prototype; demonstrate its reliability and its steady state and transient performance under prototypical inlet conditions; and deliver it to NASA JPL for further performance evaluation.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed refrigerant pump will enable reliable two-phase pumped loops for efficient and precision thermal control of critical instruments in remote sensing science satellites and exploration vehicles, including a future mission to Saturn?s moon Enceladus and the Surface Water and Ocean Topography (SWOT) mission. The pump technology also has applications in circulating condensate in water recovery systems, and in mixing and transferring cryogens and propellants in space propellant depots.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The reliable refrigerant circulation pump technology also has applications for advanced two-phase thermal control systems for high power electronics systems in commercial and military satellites and aircraft, as well as circulating pumps for chemicals, fuels, and cryogenic fluids.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Active Systems

Form Generated on 03-07-17 15:43