Minotaur I
Space launch vehicle / From Wikipedia, the free encyclopedia
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The Minotaur I, or just Minotaur is an American expendable launch system derived from the Minuteman II missile.[1] It is used to launch small satellites for the US Government, and is a member of the Minotaur family of rockets produced by Orbital Sciences Corporation (now Northrop Grumman).[2]
Space launch vehicle
![]() Minotaur I with NFIRE at MARS | |
Function | Small expendable launch system |
---|---|
Manufacturer | Northrop Grumman |
Country of origin | United States |
Size | |
Height | 19.21 metres (63.0 ft) |
Diameter | 1.67 metres (5 ft 6 in) |
Mass | 36,200 kilograms (79,800 lb) |
Stages | 4 or 5 |
Capacity | |
Payload to LEO | |
Mass | 580 kilograms (1,280 lb) |
Payload to SSO | |
Mass | 331 kilograms (730 lb) |
Launch history | |
Status | Active |
Launch sites | Vandenberg SLC-8 MARS LP-0B |
Total launches | 12 |
Success(es) | 12 |
First flight | 27 January 2000 |
Last flight | 15 June 2021 |
First stage – M55A1 | |
Powered by | 1 Solid |
Maximum thrust | 935 kilonewtons (210,000 lbf) |
Propellant | Solid |
Second stage – SR19 | |
Powered by | 1 Solid |
Maximum thrust | 268 kilonewtons (60,000 lbf) |
Propellant | Solid |
Third stage – Orion 50XL | |
Powered by | 1 Solid |
Maximum thrust | 118.2 kilonewtons (26,600 lbf) |
Burn time | 74 seconds |
Propellant | Solid |
Fourth stage – Orion 38 | |
Powered by | 1 Solid |
Maximum thrust | 34.8 kilonewtons (7,800 lbf) |
Burn time | 68 seconds |
Propellant | Solid |