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Dual Mode Green Monopropellant Propulsion System for Interplanetary Missions

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC19C0550
Agency Tracking Number: 193789
Amount: $125,000.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: T2
Solicitation Number: STTR_19_P1
Solicitation Year: 2019
Award Year: 2019
Award Start Date (Proposal Award Date): 2019-08-19
Award End Date (Contract End Date): 2020-09-18
Small Business Information
4914 Moores Mill Road
Huntsville, AL 35811-1558
United States
DUNS: 799114574
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Tomas Hasanof
 Senior Engineer
 (256) 851-7653
Business Contact
 Angela Hattaway
Phone: (256) 851-7653
Research Institution
 Georgia Institute of Technology-Main Campus
225 North Ave
Atlanta, GA 00000-0000
United States

 Federally Funded R&D Center (FFRDC)

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 nbsp;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.

* Information listed above is at the time of submission. *

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