Effect of departure delays on manned Mars mission selection

Details Effect of departure delays on manned Mars mission selection Effect of departure delays on manned Mars mission selection

Mar 1995

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995jspro..32..250d&link_type=abstract

Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 32, no. 2, p. 250-256

Other

Launch Dates, Launch Windows, Low Earth Orbits, Maneuverability, Manned Mars Missions, Manned Space Flight, Trajectory Optimization, Lunar Exploration, Nuclear Propulsion, Spacecraft Launching, Spacecraft Trajectories

Scientific paper

This study determines the effect on the initial mass in low Earth orbit (IMLEO) of 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 considered in order 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 and 1977.3 metric tons (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 than chemical propulsion. The use of a DSM does not significantly reduce the penalties. The results of this study can enable mission designers to incorporate the influence of off-nominal departure conditions of the interplanetary trajectory in the overall conceptual design of a Mars transfer vehicle.

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