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
1986
16 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Electric & Ion Propulsion , Earth orbital rendezvous , Interplanetary flight , Manned space flight , Mars landing , Mission planning , Spacecraft propulsion , Aerobraking , Atmospheric entry , Cryogenic rocket propellants , Electric propulsion , Hyperbolic reentry , Nuclear engine for rocket vehicles
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
|