Function | Heavy suborbital launch system |
---|---|
Manufacturer | Orbital Sciences |
Country of origin | United States |
Size | |
Stages | Four |
Capacity | |
Payload to 5000km S/O | |
Mass | 3,000 kilograms (6,600 lb) |
Launch history | |
Status | Canceled |
Launch sites | Vandenberg SFB, SLC-8 PSCA, LP-1 |
Total launches | 0 |
First stage – SR-118 | |
Powered by | 1 Solid |
Maximum thrust | 2,224 kilonewtons (500,000 lbf)[1] |
Specific impulse | 229 s (2.25 km/s) (sea level)[2] |
Burn time | 56.6 seconds |
Propellant | HTPB |
Second stage – SR-119 | |
Powered by | 1 Solid |
Maximum thrust | 1,223 kilonewtons (275,000 lbf)[1] |
Specific impulse | 308 s (3.02 km/s)[2] |
Burn time | 61 seconds |
Propellant | HTPB |
Third stage – SR-120 | |
Powered by | 1 Solid |
Maximum thrust | 289 kilonewtons (65,000 lbf)[1] |
Specific impulse | 300 s (2.9 km/s)[2] |
Burn time | 72 seconds |
Propellant | NEPE |
Fourth stage – Super-HAPS | |
Powered by | 12 MR-107K |
Propellant | Hydrazine |
The Minotaur III, also known as OSP-2 Target Launch Vehicle, Peacekeeper TLV, or OSP-2 TLV was an American rocket concept derived from the LGM-118 Peacekeeper missile. It was a member of the Minotaur family of rockets produced by Orbital Sciences Corporation (now part of Northrop Grumman) and would have been used for long-range suborbital launches with heavy payloads.[3] The Minotaur III was to be capable of launching 3,000 kilograms (6,600 lb) of payload 5,000 kilometres (3,100 mi) downrange.[4] This role has been taken over by the near-identical Minotaur IV Lite and the lighter-lift Minotaur II.
Minotaur III launches would have been conducted from Vandenberg Space Force Base in California and the Kodiak Launch Complex in Alaska.