Effect of Earth and Mars departure delays on human missions to Mars

Details Effect of Earth and Mars departure delays on human missions to Mars Effect of Earth and Mars departure delays on human missions to Mars

Aug 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993ads..confr....d&link_type=abstract

AAS and AIAA, Astrodynamics Specialist Conference, Victoria, Canada, Aug. 16-19, 1993, 40 p.

Other

Chemical Propulsion, Earth Orbital Environments, Earth-Mars Trajectories, Manned Mars Missions, Nuclear Propulsion, Spacecraft Trajectories, Delay, Earth-Venus Trajectories, Swingby Technique

Scientific paper

This study determines the impact on the initial mass in low-Earth orbit (IMLEO) for delaying departure from Mars and Earth by 5, 15, and 30 days, once a nominal mission to Mars has been selected. Additionally, the use of a deep space maneuver (DSM) is attempted to alleviate the IMLEO penalties. Three different classes of missions are analyzed using chemical and nuclear thermal propulsion systems in the 2000-2025 time-frame: opposition, conjunction, and fast-transfer conjunction. The results indicate that Mars and Earth delays can lead to large IMLEO penalties. Opposition and fast-transfer conjunction class missions have the highest IMLEO penalties, upwards of 432.4 mt and 1977.3 mt, respectively. Conjunction class missions, on the other hand, tend to be insensitive to Mars and Earth delays having IMLEO penalties under 103.5 mt. As expected, nuclear thermal propulsion had significantly lower IMLEO penalties as compared to chemical propulsion. The use of a DSM is found not to have a significant impact on reducing the IMLEO penalties. Through this investigation, the effect of off-nominal departure conditions on the overall mission (i.e., IMLEO) can be gained, enabling mission designers to incorporate the influence of off-nominal departure conditions of the interplanetary trajectory in the overall conceptual design process of a Mars transfer vehicle.

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