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Integrated Brayton Cryocooler for LOx and LH2 Applications

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC22CA105
Agency Tracking Number: 212328
Amount: $749,482.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: Z10
Solicitation Number: SBIR_21_P2
Timeline
Solicitation Year: 2021
Award Year: 2022
Award Start Date (Proposal Award Date): 2022-05-03
Award End Date (Contract End Date): 2024-05-02
Small Business Information
217 Billings Farm Road
White River JCT, VT 05001-9486
United States
DUNS: 080084881
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Christopher Sortore
 (802) 280-6128
 csortore@conceptsnrec.com
Business Contact
 Bradley Leiser
Phone: (802) 280-6147
Email: bleiser@conceptsnrec.com
Research Institution
N/A
Abstract

NASA is in need of affordable and robust cryogenic cooling solutions for use in space applications.nbsp; In support of the Artemis program, NASA seeks innovative integrated refrigeration cycles for use in liquefaction of hydrogen and oxygen from the lunar surface. Based on initial estimates from Phase I activities, 330+ W of cooling is needed at 90 K and 130+ W of cooling is needed at 20 K to support at least 11.7 metric tons per year.nbsp; Currently, space-based cryocoolers have yet to demonstrate cooling beyond 20 W at 20. Concepts NREC (CN) is working towards the demonstration of two high-capacity helium-based reverse-Brayton cryocoolers, and plans to leverage these cryocoolers to develop a novel integrated two-stage helium system capable of supporting both oxygen and hydrogen liquefaction needs on the Moon. The proposed solution will increase the current state-of-the-art in cryogenic cooling by an order of magnitude. The two lowest TRL/MRL components derived from Phase I activities are a micro-tube recuperator with a titanium construction replacing the legacy materials, and a compressor capable of operation under lunar surface ambient conditions. The titanium micro-tube recuperators utilize a proven, underlying design; the same manufacturing method and models can easily be adapted to the changes brought upon by the change to titanium, and development risk is considered low. Lunar ambient compressor operation has the highest system risk when looking at the changes from legacy CN demonstrations. Existing turboalternator powertrain technology will be leveraged to develop a compressor powertrain that is capable of operation at the reduced ambient conditions. The capabilities of the newly developed powertrain will need to handle larger thrust loads at higher rotational speeds than what is currently found on the turboalternators. Results from this study will provide valuable input into NASArsquo;s on-going Cryogenic Fluid Management directives.

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

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