A Systematic Approach for the End-to-End Configuration Optimization of Manned Missions to the Moon
- Paper number
IAC-07-D3.3.05
- Author
Dr. Shyama Chakroborty, Northrop Grumman Corporation, United States
- Coauthor
- Coauthor
Jim Berry, Northrop Grumman Corporation, United States
- Year
2007
- Abstract
A renewed interest in manned missions to the moon and Mars has led the way for a number of recent initiatives by NASA and other organizations. NASA has set the goal for a manned mission to the moon as early as 2020 as part of its Constellation program with Mars missions to follow after that. In order to maximize the up- and down-cargo for these missions, the configurations for all the elements of the Constellation program need to be optimized for weight while meeting reliability requirements at the lowest possible cost. The size of the payload, mission duration and exploration objectives on the surface of the moon and Mars will have a direct impact on the size and configuration of all the elements. These elements include the launch vehicle and other elements responsible for Trans Lunar Injection (TLI), Lunar Orbit Insertion (LOI), descent to the lunar surface, functions at the lunar surface, ascent from the lunar surface and rendezvous with an orbiting Crew Exploration Vehicle (CEV) for return of astronauts and cargo to Earth. This paper describes a systems approach and methodology to identify weight growth sensitivities of each of these elements and the related optimization scheme to reduce weight in selected areas to establish mass-optimized configurations for the end-to-end mission. Cost minimization and reliability budgeting to assure affordable and safe missions will also be discussed.
- Abstract document
- Manuscript document
IAC-07-D3.3.05.pdf (🔒 authorized access only).
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