Multi-mission Modular Spacecraft
Multi-mission Modular Spacecraft is a NASA design of modular spacecraft, intended to save cost and ease servicing.[1][2][3]
MMS was intended to be "Shuttle compatible", i.e. recoverable/serviceable by the Space Shuttle orbiter.[3]
It was used for:[4]
- Solar Maximum Mission (SMM), 1980
- Landsat 4, 1982
- Landsat 5, 1984
- Upper Atmosphere Research Satellite (UARS), 1991
- Extreme Ultraviolet Explorer (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
References
- Multi-mission Modular Spacecraft (MMS)
- The Multi-mission Modular Spacecraft for the 80's
This article incorporates text from this source, which is in the public domain. - NASA standard Multi-mission Modular Spacecraft for future space exploration This article incorporates text from this source, which is in the public domain.
- 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.CS1 maint: multiple names: authors list (link)
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