Minotaur III
| Function | Heavy suborbital launch system |
|---|---|
| Manufacturer | Orbital Sciences |
| Country of origin |
 United States |
| Size | |
| Stages | Four |
| Capacity | |
| Payload to 5000km S/O | 3,000 kilograms (6,600 lb) |
| Launch history | |
| Status | Development |
| Launch sites |
Vandenberg Kodiak |
| First stage - SR-118 | |
| Engines | 1 Solid |
| Thrust | 1,607 kilonewtons (361,000 lbf) |
| Burn time | 83 seconds |
| Fuel | Solid |
| Second stage - SR-119 | |
| Engines | 1 Solid |
| Thrust | 1,365 kilonewtons (307,000 lbf) |
| Burn time | 54 seconds |
| Fuel | Solid |
| Third stage - SR-120 | |
| Engines | 1 Solid |
| Thrust | 329 kilonewtons (74,000 lbf) |
| Burn time | 62 seconds |
| Fuel | Solid |
| Fourth stage - Super-HAPS | |
| Engines | 12 MR-107K |
| Fuel | Hydrazine |
The Minotaur III, also known as OSP-2 Target Launch Vehicle, Peacekeeper TLV or OSP-2 TLV is an American rocket derived from the LGM-118 Peacekeeper missile. It is a member of the Minotaur family of rockets produced by Orbital Sciences Corporation, and is used for long range suborbital launches with heavy payloads.
Minotaur III rockets consist of four stages; the SR-118 first stage, SR-119 second stage and SR-120 third stage of a decommissioned Peacekeeper missile, with a Super-HAPS fourth stage, derived from the HAPS stage used on Pegasus and Minotaur I rockets. The Minotaur III is capable of launching a 3,000 kilograms (6,600 lb) payload 5,000 kilometres (3,100 mi) downrange on a suborbital trajectory.
Minotaur III launches will be conducted from Vandenberg Air Force Base and the Kodiak Launch Complex.
References
- "Fact Sheet" (PDF). Minotaur III. Orbital Sciences Corporation. Retrieved 2009-05-06.
- Wade, Mark. "Minotaur". Encyclopedia Astronautica. Retrieved 2009-05-06.
- Krebs, Gunter. "Minotaur-3 (OSP-2 Peacekeepr TLV)". Gunter's Space Page. Retrieved 2009-05-06.
- Krebs, Gunter. "Minotaur-3/-4/-5 (OSP-2 Peacekeeper SLV)". Gunter's Space Page. Retrieved 2009-05-06.