Minotaur V
The Minotaur V is an American expendable launch system derived from the Minotaur IV, itself a derivative of the LGM-118 Peacekeeper ICBM. It was developed by Orbital Sciences Corporation, (now absorbed into Northrop Grumman Innovation Systems) and made its maiden flight on 7 September 2013 carrying the Lunar Atmosphere and Dust Environment Explorer spacecraft for NASA.
The first Minotaur V at MARS before the launch of LADEE. | |
| Function | Expendable launch system |
|---|---|
| Manufacturer | Northrop Grumman (Northrop Grumman Innovation Systems) |
| Country of origin | United States |
| Size | |
| Height | 24.56 m |
| Diameter | 2.34 m |
| Mass | 89,373 kg |
| Stages | Five |
| Capacity | |
| Payload to GTO | |
| Mass | 532 kg |
| Payload to TLI | |
| Mass | 342 kg |
| Associated rockets | |
| Family | Minotaur |
| Launch history | |
| Status | Active |
| Launch sites | SLC-8, Vandenberg AFB LP-0B, MARS LP-1, Kodiak |
| Total launches | 1 |
| Success(es) | 1 |
| First flight | 7 September 2013 |
| First stage – SR-118 | |
| Powered by | 1 Solid |
| Maximum thrust | 2,200 kN (490,000 lbf) |
| Burn time | 83 seconds |
| Propellant | Solid |
| Second stage – SR-119 | |
| Powered by | 1 Solid |
| Maximum thrust | 1,365 kilonewtons (307,000 lbf) |
| Burn time | 54 seconds |
| Propellant | Solid |
| Third stage – SR-120 | |
| Powered by | 1 Solid |
| Maximum thrust | 329 kilonewtons (74,000 lbf) |
| Burn time | 62 seconds |
| Propellant | Solid |
| Fourth stage – Star-48BV | |
| Powered by | 1 Solid |
| Maximum thrust | 64 kilonewtons (14,000 lbf) |
| Burn time | 84 seconds |
| Propellant | Solid |
| Fifth stage (Baseline) – Star-37FM | |
| Powered by | 1 Solid |
| Maximum thrust | 47.26 kilonewtons (10,620 lbf) |
| Burn time | 63 seconds |
| Propellant | Solid |
| Fifth stage (Optional) – Star-37FMV | |
| Powered by | 1 Solid |
| Propellant | Solid |
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