Assessment of MON-25/MMH Propellant System for Deep-Space Engines

Trinh, Huu P ; Burnside, Christopher ; Williams, Hunter

关键词: DEEP SPACE;    ENGINE DESIGN;    FLYBY MISSIONS;    LIQUID ROCKET PROPELLANTS;    LOW TEMPERATURE;    MISSION PLANNING;    NITRIC OXIDE;    NITROGEN TETROXIDE;    OPERATING TEMPERATURE;    OXIDIZERS;    PROPULSION SYSTEM CONFIGURATIONS;    PROPULSION SYSTEM PERFORMANCE;    ROBUSTNESS (MATHEMATICS);    SYSTEMS ENGINEERING;   

RP-ID  :  M19-7648

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

Hypergolic 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.