Engineering:MultiMission Modular Spacecraft
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MultiMission Modular Spacecraft is a NASA design of modular spacecraft, intended to save cost and ease servicing.[1][2][3] MMS were intended to be 'Shuttle compatible', i.e. recoverable/serviceable by the Space Shuttle orbiter.[3]
It was used for:[4]
- Solar Maximum Mission, 1980
- Landsat 4, 1982
- Landsat 5, 1984
- UARS, 1991
- EUVE, 1992
- TOPEX/Poseidon, 1992 [5]
Component modules
Basic modules:[1]
- Modular Attitude Control Subsystem (MACS)
- Power module
- Command and Data Handling - (using the NSSC-1 computer for at least the first three.[6])
all mounted on a triangular module support structure.
Optional modules:[1]
- Propulsion module
- Instrument module interface (Ring)
- Space Shuttle Remote Manipulator System (SSRMS) Grapple Fixture
See also
References
- ↑ 1.0 1.1 1.2 Multimission modular spacecraft (MMS)
- ↑ The Multimission Modular Spacecraft for the 80's
- ↑ 3.0 3.1 NASA standard Multimission Modular Spacecraft for future space exploration[|permanent dead link|dead link}}]
- ↑ Fairchild: MMS (Multi-Mission Modular Spacecraft)
- ↑ TOPEX/Poseidon: Perspectives on an Ocean Planet - MMS
- ↑ Trevathan, Charles E., Taylor, Thomas D., Hartenstein, Raymond G., Merwarth, Ann C., and Stewart, William N. (1984). "Development and Application of NASA’s First Standard Spacecraft Computer". Communications of the ACM 27 (9): 902–913. doi:10.1145/358234.358252. http://fermatslibrary.com/s/development-and-application-of-nasas-first-standard-spacecraft-computer.
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