Integrated Composite Rocket Nozzle Extension

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$125,000.00
Award Year:
2013
Program:
SBIR
Phase:
Phase I
Contract:
NNX13CC35P
Award Id:
n/a
Agency Tracking Number:
124273
Solicitation Year:
2012
Solicitation Topic Code:
H2.02
Solicitation Number:
n/a
Small Business Information
WI, Madison, WI, 53717-1961
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
196894869
Principal Investigator:
RobertGustafson
Principal Aerospace Engineer
(608) 229-2725
gustafsonr@orbitec.com
Business Contact:
EricRice
Business Official
(608) 229-2804
knaufs@orbitec.com
Research Institute:
Stub




Abstract
ORBITEC proposes to develop and demonstrate an Integrated Composite Rocket Nozzle Extension (ICRNE) for use in rocket thrust chambers. The ICRNE will utilize an innovative bonding approach to join a high-temperature composite nozzle extension to a regeneratively cooled metallic nozzle. The ICRNE technology will allow high-temperature composite materials to be directly integrated into a regeneratively-cooled nozzle section or thrust chamber made out of high-strength metallic alloys, thereby eliminating the heavy bolted flange joint that is currently used to attach high-temperature nozzle extensions. The resulting weight reduction will increase the thrust-to-weight ratio of the rocket engine. The ICRNE will also eliminate the need for multiple seals in the bolted flange joints, thus increasing reliability. The focus of the proposed Phase 1 effort will be to demonstrate the ICRNE technology by manufacturing and evaluating test specimens. A prototype ICRNE will also be designed and analyzed. In Phase 2, a prototype ICRNE unit will be fabricated, installed, and hot fire tested on an existing rocket engine. This proposal responds to Subtopic H2.02 In-Space Propulsion Systems, specifically "high temperature materials, coatings and/or ablatives or injectors, combustion chambers, nozzles, and nozzle extensions" for non-toxic, cryogenic, and nuclear thermal propulsion systems.

* information listed above is at the time of submission.

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