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Low-Cost, High-Performance Combustion Chamber for LOX/CH4 Propulsion

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX10CD15P
Agency Tracking Number: 095364
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: X10.01
Solicitation Number: N/A
Timeline
Solicitation Year: 2009
Award Year: 2010
Award Start Date (Proposal Award Date): 2010-01-29
Award End Date (Contract End Date): 2010-07-29
Small Business Information
12173 Montague Street
Pacoima, CA 91331-2210
United States
DUNS: 052405867
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Arthur Fortini
 Principal Investigator
 (818) 899-0236
 art.fortini@ultramet.com
Business Contact
 Craig Ward
Title: Engineering Administrative Mgr
Phone: (818) 899-0236
Email: craig.ward@ultramet.com
Research Institution
N/A
Abstract

Ultramet will design and fabricate a lightweight, high temperature 5-lbf combustion chamber for use with cryogenic liquid oxygen/methane (LOX/CH4) propellant that will deliver a specific impulse of ~355 seconds, an increase over the current 320-sec baseline that will result in a propellant mass decrease of 55 lbm. The material system will be based on Ultramet's proven oxide-iridium/rhenium architecture, which has been successfully hot-fire tested with stoichiometric oxygen/hydrogen for hours. Instead of rhenium, however, the structural material will be a niobium alloy that has excellent high temperature yield strength. With a yield strength-to-weight ratio over 33% greater than that of rhenium at elevated temperature, this niobium alloy will significantly reduce chamber weight. The starting materials are two orders of magnitude less expensive than rhenium and are less expensive than the C103 alloy commonly used in low-performance engines. Aerojet will design the chamber in Phase I and will perform hot-fire testing in Phase II. Phase II will include scaleup of the process and testing of a chamber in the 25- to 500-lbf thrust class, which would be suitable for a reaction control system engine on a lunar ascent/descent vehicle.

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

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