NASA STTR 2019-I Solicitation

Proposal Summary

 19-1- T2.03-3789
 Performance Demonstration of High Payoff Propulsion Technology: Rotating Detonation Engine and Dual Mode Ionic Liquid
 Dual Mode Green Monopropellant Propulsion System for Interplanetary Missions
Name:  Plasma Processes, LLC
Name:  Georgia Institute of Technology-Main Campus
Street:  4914 Moores Mill Road
Street:  505 Tenth Street NW
City:  Huntsville
City:  Atlanta
State/Zip:  AL 35811-1558
State/Zip:  GA 30332-0420
PHONE:  (256) 851-7653
PHONE:  (404) 594-0950

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

Mr. Tomas Hasanof
4914 Moores Mill Road Huntsville, AL 35811 - 1558
(256) 851-7653

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

Mr. Timothy McKechnie
4914 Moores Mill Road Huntsville, AL 35811 - 1558
(256) 851-7653
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Today many spacecraft carry two propulsion options: high thrust required for high acceleration maneuvers such as orbit insertion and rapid response; and low thrust required for station keeping and less critical maneuvers. A new class of non-toxic monopropellants, such as AF-M315E and LMP-103S, perform well in both high and low thrust regimes. Significant investments are maturing both monopropellants into propulsion systems tailored for each option. Of interest is leveraging these new technologies into a common propellant, dual mode propulsion system with  integrated system design and performance.

In support of this concept, Plasma Processes will design an AF-M315E-based dual mode propulsion system in cooperation with Georgia Tech. The baseline system is an extended 4-unit CubeSat propulsion module with four 100 mN thrusters for roll, pitch, and yaw maneuvers; and one 5N thruster for Delta-V maneuvers. The propulsion module is easily expanded to an 8-unit module, allowing for more propellant and longer missions.

Non-toxic monopropellants are positioned to provide increased mission safety, reduced life cycle costs, and increased performance over state-of-the-art alternatives. From a spacecraft perspective, a single propellant, dual mode propulsion system can reduce weight and volume, allowing for more payload and greater propulsion flexibility. From a mission perspective, the technology facilitates the use of less expensive launch vehicles, less stringent launch requirements, and transfer to desired orbit. This concept enables frequent low-cost missions allowing for iteration and opportunities to improve technologies.

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

Interplanetary Deep Space Exploration (AEOLUS, CUVE, CHARIOT), Asteroid Exploration (ROSS, APEX), Lunar Exploration (CUBEX), Earth Science & Observation

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

Earth Observation (PLANET LABS), Satellite De-Orbit De-commissioning & Escape Orbits, Global Connectivity (OneWeb, STARLINK/SpaceX, Athena/Facebook), Science & Technology Missions (NOAA), Low Cost Launch Providers

Duration: 6

Form Generated on 06/16/2019 22:57:55