Minotaur I

Minotaur I
Minotaur I with NFIRE at MARS
FunctionSmall expendable launch system
ManufacturerNorthrop Grumman
Country of originUnited States
Size
Height19.21 metres (63.0 ft)
Diameter1.67 metres (5 ft 6 in)
Mass36,200 kilograms (79,800 lb)
Stages4 or 5
Capacity
Payload to LEO
Mass580 kilograms (1,280 lb)
Payload to SSO
Mass331 kilograms (730 lb)
Launch history
StatusActive
Launch sitesVandenberg SLC-8
MARS LP-0B
Total launches13
Success(es)13
First flight27 January 2000
Last flight18 June 2024
First stage – M55A1
Powered by1 Solid
Maximum thrust935 kilonewtons (210,000 lbf)
PropellantSolid
Second stage – SR19
Powered by1 Solid
Maximum thrust268 kilonewtons (60,000 lbf)
PropellantSolid
Third stage – Orion 50XL
Powered by1 Solid
Maximum thrust118.2 kilonewtons (26,600 lbf)
Burn time74 seconds
PropellantSolid
Fourth stage – Orion 38
Powered by1 Solid
Maximum thrust34.8 kilonewtons (7,800 lbf)
Burn time68 seconds
PropellantSolid

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]

  1. ^ Cite error: The named reference minotaur-factsheet was invoked but never defined (see the help page).
  2. ^ "Minotaur Rocket". Northrop Grumman. Retrieved 2021-06-07.