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The National Technical Information Service acquires, indexes, abstracts, and archives the largest collection of U.S. government-sponsored technical reports in existence. The NTRL offers online, free and open access to these authenticated government technical reports. Technical reports and documents in its repository may be available online for free either from the issuing federal agency, the U.S. Government Publishing Office’s Federal Digital System website, or through search engines.

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Rapid MARS Transits with Exhaust-Modulated Plasma Propulsion.

N9619285

Publication Date	1995
Personal Author	Chang-diaz, F. R.; Braden, E.; Johnson, I.; Hsu, M. M.; Yang, T. F.
Page Count	16
Abstract	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.
Keywords	Earth-mars trajectories Manned mars missions Mars (Planet) Mars exploration Mars probes Mission planning Plasma propulsion Robotics Payloads Propulsion system configurations Propulsion system performance Specific impulse Trajectory optimization
Source Agency	National Aeronautics and Space Administration
NTIS Subject Category	84 - Space Technology
Corporate Authors	National Aeronautics and Space Administration, Houston, TX. Lyndon B. Johnson Space Center.
Document Type	Technical Report
NTIS Issue Number	199613

Rapid MARS Transits with Exhaust-Modulated Plasma Propulsion.

Rapid MARS Transits with Exhaust-Modulated Plasma Propulsion.
N9619285

Publication Date	1995
Personal Author	Chang-diaz, F. R.; Braden, E.; Johnson, I.; Hsu, M. M.; Yang, T. F.
Page Count	16
Abstract	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.
Keywords	Earth-mars trajectories Manned mars missions Mars (Planet) Mars exploration Mars probes Mission planning Plasma propulsion Robotics Payloads Propulsion system configurations Propulsion system performance Specific impulse Trajectory optimization
Source Agency	National Aeronautics and Space Administration
NTIS Subject Category	84 - Space Technology
Corporate Authors	National Aeronautics and Space Administration, Houston, TX. Lyndon B. Johnson Space Center.
Document Type	Technical Report
NTIS Issue Number	199613