Manned Mars stopover missions of 12 to 15 mo duration are characterized by Earth return velocities ranging up to 68,000 fps over cycle of mission opportunities; promising mode for reducing Earth entry velocities to 40,000 to 53,000 fps without increasing spacecraft gross weight is swing-by through gravitational field of Venus; technique can be applied to all Mars mission opportunities, and in about one-third of them, propulsion requirements can be reduced below minimum direct mode values; possible spacecraft configurations are presented, typical trajectory paths indicated, and tradeoffs between Earth velocity, trip duration, and propulsion requirements shown.
Manned Mars trips using Venus flyby modes
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 3 , n 2
1966
9 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Manned Mars trips using Venus flyby modes.
NTRS | 1966
|Manned Mars trips using Venus flyby modes.
AIAA | 1966
|Manned mars trips using venus swingby modes.
NTRS | 1964
|MANNED MARS TRIPS USING VENUS SWINGBY MODES
AIAA | 1964
|Mars/Venus flyby missions with manned Mars landers.
AIAA | 1967
|