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Assessment of MON-25/MMH Propellant System for Deep-Space EnginesHypergolic propellant system of oxidizer MON-25 and fuel MMH has been considered in propulsion trade studies for NASA science mission concepts. A propulsion system using this bi-propellant combination will be capable of operating at a lower temperature as compared to traditional MON-3/MMH for heater power reduction. Operation robustness can also be realized since such a propellant system is utilized under a wide range of temperatures. Propulsion system designs and engine test programs for MON-25/MMH have been carried out since 2008. Several engine development programs have been conducted. The thrust classes of 22-Newton [5-lb(sub f)] and 445-Newton [100-lb(sub f)] were tested with the capability of a pulse mode operation for a wide range of duty cycles. Additional engine development tests are followed. Outcomes of the development efforts suggest that there is a balance of mission benefits and potential engine design and operation challenges, although the propellants can handle a low temperature. This paper will report an assessment of using the MON-25/MMH system for deep- space application.

Document ID
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Trinh, Huu P.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Burnside, Christopher
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Williams, Hunter
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
December 1, 2019
Publication Date
October 21, 2019
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
Meeting Information
Meeting: International Astronautical Congress (IAC)
Location: Washington, DC
Country: United States
Start Date: October 21, 2019
End Date: October 25, 2019
Sponsors: International Astronautical Federation (IAF-HQ)
Distribution Limits
Work of the US Gov. Public Use Permitted.
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