NASA SBIR 2012 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 12-1 H2.02-9727
SUBTOPIC TITLE: In-Space Propulsion Systems
PROPOSAL TITLE: Integrated Composite Rocket Nozzle Extension

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Orbital Technologies Corporation
Space Center, 1212 Fourier Drive
Madison, WI 53717 - 1961
(608) 827-5000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Gustafson
gustafsonr@orbitec.com
1212 Fourier Dr.
Madison, WI 53717 - 1961
(608) 229-2725

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Eric Rice
knaufs@orbitec.com
Space Center, 1212 Fourier Drive
Madison, WI 53717 - 1961
(608) 229-2804

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

Technology Available (TAV) Subtopics
In-Space Propulsion 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)
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.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The ICRNE technology addresses the needs of Subtopic H2.02 In-Space Propulsion Systems, which requests "high temperature materials, coatings and/or ablatives or injectors, combustion chambers, nozzles, and nozzle extension." We expect the ICRNE technology to have direct and immediate application for RCS thrusters, OMS engines, upper stage engines, planetary ascent and descent engines, and new booster engines.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Beyond the needs of NASA, the DOD also requires advanced nozzle technology for new upper stage engines and boosters. If successful, the ICRNE technology can be used to join dissimilar materials for a very broad range of applications in many industries, including wing leading edges for high speed transport aircraft, airbreathing engines, turbines, industrial burners, and corrosion-resistant structures for naval vessels.

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.)
Atmospheric Propulsion
Joining (Adhesion, Welding)
Processing Methods
Spacecraft Main Engine


Form Generated on 03-28-13 15:21