NEP mission sensitivities to system performance | Zendy

James H. Gilland | Zendy

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NEP mission sensitivities to system performance

Author(s) -

James H. Gilland

Publication year - 1992

Publication title -

aip conference proceedings

Language(s) - English

Resource type - Conference proceedings

SCImago Journal Rank - 0.177

H-Index - 75

eISSN - 1551-7616

pISSN - 0094-243X

DOI - 10.1063/1.41736

Subject(s) - propulsion , specific impulse , mars exploration program , aerospace engineering , electrically powered spacecraft propulsion , impulse (physics) , range (aeronautics) , systems engineering , technology readiness level , computer science , aeronautics , environmental science , physics , engineering , astrobiology , quantum mechanics

Nuclear Electric Propulsion (NEP) mission performance is strongly affected by system performance. Power and propulsion system specific mass, specific impulse, and efficiency all combine to determine the performance limits for a given mission. Thruster technology determines the specific impulse and efficiency of the system. The effects of these parameters on the mission performance of NEP systems relative to other concepts has been analyzed to give guidance to thruster development goals for a range of missions: Lunar Cargo, Mars Cargo, and Mars Piloted. Mission sensitivities to system parameters are discussed, and technology requirements are identified for each mission.

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