MultiMission Modular Spacecraft
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]
- (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)
- (SSRMS) Grapple Fixture
See also[]
References[]
- ^ Jump up to: a b c Multimission modular spacecraft (MMS)
- ^ The Multimission Modular Spacecraft for the 80's
- ^ Jump up to: a b NASA standard Multimission Modular Spacecraft for future space exploration[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.CS1 maint: multiple names: authors list (link)
 | This spacecraft or satellite related article is a stub. You can help Wikipedia by . |
Categories:
- NASA satellites
- Spacecraft components
- Spacecraft design
- Spacecraft stubs