A number of manned Mars mission types, propulsion systems, and operational techniques are compared. Conjunction and opposition class missions for cryogenic, hybrid (cryo/storable), and NERVA propulsion concepts are addressed. In addition, both Earth and Mars orbit aerobraking, direct entry of landers, hyperbolic rendezvous, and electric propulsion cases are examined. A common payload to Mars was used for all cases. The basic figure of merit used was weight in low Earth orbit (LEO) at mission initiation. This is roughly proportional to launch costs.
Comparison of Mission Design Options for Manned Mars Missions
Manned Mars Missions Workshop ; 1985 ; Huntsville, AL, US
1986-05-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Trajectory Options for Manned Mars Missions
AIAA | 2002
|Trajectory Options for Manned Mars Missions
Online Contents | 2005
|Trajectory Options for Manned Mars Missions
AIAA | 2005
|