Computer Science – Performance
Scientific paper
Jul 1993
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993ida..rept.....f&link_type=abstract
Final Report, Dec. 1989 - Jul. 1991 Institute for Defense Analyses, Alexandria, VA.
Computer Science
Performance
Aerobraking, Atmospheric Entry, Earth-Mars Trajectories, Manned Spacecraft, Nuclear Engine For Rocket Vehicles, Orbital Velocity, Propulsion System Configurations, Propulsion System Performance, Space Shuttle Main Engine, Transit Time, Aerocapture, High Speed, Orbital Mechanics, Rendezvous Spacecraft, Space Transportation, Spacecraft Propulsion
Scientific paper
Propulsion systems composed of a Shuttle External Tank, appropriately modified for the purpose, with a rocket engine that is either an SSME or a NERVA could inject a gross personnel payload of 100,000 lb on a trans-Mars trajectory from Space Station Freedom with aerobraking at Mars with transit times of less that 70 days. Such transit times reflect a significant reduction from the 200-plus days generally considered. The 100,000-lb payload would include the mass of a hypothetical aerobrake for aerocapture at Mars. The entry velocities at Mars compatible with such transit times are greater that 21 km/sec, to be compared with previously stated constraints of 8.5 to 9.5 km/sec for nominal Mars entry velocity. Limits of current aerobrake technology are not well enough defined to determine the feasibility of an aerobrake to handle Mars-entry velocities for short-transit-time trajectories. Return from Mars to Earth on a mirror image of 70-days outbound trajectory (consistent with a stay time of about 12 days) would require a Mars-departure velocity increment more than twice as great as that at Earth departure and would require a correspondingly more capable propulsion system. The return propulsion system would preferably be pre-deployed at Mars by one or more separate minimum-energy, 0.5 to 1.1 Mlb gross payload cargo flights with the same outbound propulsion systems as the personnel flight, before commitment of the personnel flight. Aerobraking entry velocity at Earth after such a transit time would be about 16 km/sec, to be compared with constraints set at 12.5 to 16 km/sec.
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