NASA Technical Reports Server (NASA) · 1995 · 43 citations · 4 references
Open access
Space VehicleEngineeringPlasma PhysicsRobotic Mission ScenariosSpace TransportationSpace VehiclesSystems EngineeringSpace Flight SystemsSpace MissionsMechatronicsConstant PowerRocket EngineAerospace Propulsion SystemsPropulsionRapid MarsIon PropulsionAerospace EngineeringExhaust-modulated Plasma RocketAerospace PropulsionPayload Design
The operational characteristics of the Exhaust-Modulated Plasma Rocket are described. Four basic human and robotic mission scenarios to Mars are analyzed using numerical optimization techniques at variable specific impulse and constant power. The device is well suited for 'split-sprint' missions, allowing fast, one-way low-payload human transits of 90 to 104 days, as well as slower, 180-day, high-payload robotic precursor flights. Abort capabilities, essential for human missions, are also explored.
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