NASA SBIR 2009 Solicitation


PROPOSAL NUMBER: 09-1 X10.01-9928
SUBTOPIC TITLE: Cryogenic and Non-Toxic Storable Propellant Space Engines
PROPOSAL TITLE: UCDS Based Stable Injector Design

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Gloyer-Taylor Laboratories LLC
2212 Harton Blvd
Tullahoma, TN 37388 - 5583
(931) 393-5108

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Paul Gloyer
2212 Harton Blvd
Tullahoma, TN 37388 - 5583
(931) 393-5108

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

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
The Universal Combustion Device Stability (UCDS) Process is the culmination of more than 40 years of research and provides the means to understand the complex dynamics and processes inside any chemical propulsion system, including liquid rockets, solid rockets, hybrid rockets, turbojet combustors and augmentors, and even scramjets. In addition to predicting whether a combustion chamber will oscillate and how large the amplitude of the oscillation will be, UCDS provides insight into WHY a device oscillates. With this type understanding, it is possible to design for stability in any chemical rocket, turbojet or scramjet.
GTL proposes to apply the UCDSTM Process to create a clean-sheet design for a new stable liquid rocket engine that is suitable to use as an Ascent Engine for Altair. Rather than starting with preconceived notions or heritage constraints, GTL shall exercise the UCDS tools to establish detailed injector design guidelines that will ensure stable operation.
This will include definition of functions that define mass injection distribution, vaporization/atomization profile, heat release characteristics, feed system response and many other parameters. By following these requirements in an injector design, the mechanisms that drive oscillations will be minimized, while the damping mechanisms are maximized, thereby maximizing stability margin.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The UCDS process can be used to aid in the development of NASA rockets (solid, liquid or hybrid), turbojets or scramjets. The specific design guidelines for stability that are being developed in the proposed effort can be applied to support the development of the lunar ascent engine for Altair. The results may also explain why the CECE engine behaves the way it does and why the selected oscillation mitigation technique is effective.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The UCDS process can be used to reduce development cost of practically any chemical propulsion system. This capability could be used to support a wide variety of DoD propulsion development efforts, including rockets, turbojet augmentors or scramjets. UCDS can also be applied to support commercial engine development.

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.

Aircraft Engines
Simulation Modeling Environment

Form Generated on 09-18-09 10:14