Minotaur I
Minotaur familyOrbital Sciences CorporationActive
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
- LEO capacity
- 580 kg
- SSO capacity
- 331 kg
Specifications from Launch Library. Figures the operator has not published are omitted.
Flight record
First flight January 27, 2000 · latest June 15, 2021
Counted from padside's own launch record, the same basis as the stats page.
Flights per year
- Successful
- Failed
Show the numbers for Minotaur I flights per year
| Year | Successful | Failed | Total |
|---|---|---|---|
| 2000 | 2 | 0 | 2 |
| 2001 | 0 | 0 | 0 |
| 2002 | 0 | 0 | 0 |
| 2003 | 0 | 0 | 0 |
| 2004 | 0 | 0 | 0 |
| 2005 | 2 | 0 | 2 |
| 2006 | 2 | 0 | 2 |
| 2007 | 1 | 0 | 1 |
| 2008 | 0 | 0 | 0 |
| 2009 | 1 | 0 | 1 |
| 2010 | 0 | 0 | 0 |
| 2011 | 2 | 0 | 2 |
| 2012 | 0 | 0 | 0 |
| 2013 | 1 | 0 | 1 |
| 2014 | 0 | 0 | 0 |
| 2015 | 0 | 0 | 0 |
| 2016 | 0 | 0 | 0 |
| 2017 | 0 | 0 | 0 |
| 2018 | 0 | 0 | 0 |
| 2019 | 0 | 0 | 0 |
| 2020 | 0 | 0 | 0 |
| 2021 | 1 | 0 | 1 |