NASA STTR 2019-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 19-1- T2.03-2452
SUBTOPIC TITLE:
 Performance Demonstration of High Payoff Propulsion Technology: Rotating Detonation Engine and Dual Mode Ionic Liquid
PROPOSAL TITLE:
 Demonstration of Dual Mode Ionic Liquid Propulsion
SMALL BUSINESS CONCERN (SBC):
RESEARCH INSTITUTION (RI):
Name:  Streamline Automation, LLC
Name:  University of Tennessee Space Institute
Street:  3100 Fresh Way Southwest
Street:  411 B.H. Goethert Pkwy
City:  Huntsville
City:  Tullahoma
State/Zip:  AL 35805-6720
State/Zip:  TN 37388-4002
PHONE:  (256) 694-5063
PHONE:  (931) 393-7351

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Geoffrey Chew Ph.D.
E-mail:
geoffrey.chew@streamlineautomation.biz
Address:
3100 Fresh Way Southwest Huntsville, AL 35805 - 6720
Phone:
(256) 713-1220

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Alton Reich
E-mail:
Alton.Reich@StreamlineAutomation.biz
Address:
3100 Fresh Way Southwest Huntsville, AL 35805 - 6720
Phone:
(256) 713-1220
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

This program will design, fabricate, and test a dual mode propulsion system in a non-flight-weight configuration using a novel energetic, low-toxicity ionic liquid for both high thrust (conventional catalyst-based monopropulsion system) and low thrust (electrospray) engines. Non-Stoichiometric HydroxyEthyl Hydrazinium Nitrate (NSHEHN), developed under Army and NASA SBIR programs, will be used for both engines. It is favored over hydrazine for monopropellant systems because of its very low vapor pressure which makes it much less toxic. The advantage over the Air Force-developed monopropellant, AF-M315E, is that it uses a conventional catalyst bed at 200ºC compared to an expensive specialized catalyst bed at over 500ºC. It is particularly applicable to electrospray propulsion because it is already composed of ions does not require energy to convert a non-ionic fluid to an ionic state. The two engines will be designed and tested separately and a breadboard system designed for use in Phase II.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Application of C3 Propulsion’s Ionic Liquid propulsion technology will be applicable throughout NASA. In particular, it will be of use in satellite insertion and station keeping, manned and unmanned attitude control, advanced space station, propulsion for Lunar and Mars missions, and deep space robotic missions. The dual mode operation will reduce the size and weight of systems that use separate high and low thrust engines. The ionic liquid reduces the life cycle/logistics costs and lowers the catalyst bed power requirements.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

C3 Propulsion's Ionic Liquid technology is useful for any missile or satellite station keeping applications as a low toxicity replacement for conventional hydrazine-based monopropellants, as well as DoD specific needs including tactical, air-to-air, air-to-ground, and ballistic missile defense applications. Satellite manufacturers would be interested for position and station keeping abilities.

 

 

Duration: 13

Form Generated on 06/16/2019 23:00:43