The Minotaur I launch system is derived from converted Minuteman II ICBMs and is used to launch small satellites for the US Government. The first and second stages, taken directly from decommissioned Minuteman missiles, are mated to the Orion third and fourth stages taken from the Pegasus XL air-launched rocket family. An optional hydrazine-powered fifth stage called HAPS can be used.The Minotaur I launch system is derived from converted Minuteman II ICBMs and is used to launch small satellites for the US Government. An optional hydrazine-powered fifth stage called HAPS can be used.
Specifications
- Thrust
- 935 kN
- Height
- 19.21 m
- Diameter
- 1.67 m
- Launch mass
- 36 t
- Stages
- 5
- Launch cost
- —
- LEO capacity
- 580 kg
- GTO capacity
- —
- GEO capacity
- —
- SSO capacity
- 331 kg
Vehicle specifications from Launch Library; blanks are unpublished figures.
Flight record
Flights
12
Launches with a definitive outcome
Success rate
100%
12 of 12
Current success streak
12
Landings
0
0 attempts · 0 droneship / 0 RTLS
Fastest turnaround
—
Between consecutive booster flights
Counted from padside's own launch record — the same basis as the Stats page.
Launches
- Minotaur I | NROL-111 — Success
- Minotaur I | ORS-3 — Success
- Minotaur I | ORS-1 (USA-231) — Success
- Minotaur I | NROL-66 (RPP) (USA-225) — Success
- Minotaur I | Tacsat 3 — Success