Minotaur III
title: "Minotaur III" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["minotaur-(rocket-family)"] topic_path: "general/minotaur-rocket-family" source: "https://en.wikipedia.org/wiki/Minotaur_III" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0
::data[format=table title="Infobox Rocket"]
| Field | Value |
|---|---|
| name | Minotaur III |
| function | Heavy suborbital launch system |
| manufacturer | Orbital Sciences |
| country-origin | United States |
| stages | Four |
| location | 5000km S/O |
| kilos | 3000 kg }} |
| status | Canceled |
| sites | Vandenberg SFB, SLC-8 |
| PSCA, LP-1 | |
| launches | 0 |
| type | stage |
| stageno | First |
| name | SR-118 |
| engines | 1 Solid |
| thrust | 2224 kN |
| SI | 229 isp (sea level) |
| burntime | 56.6 seconds |
| fuel | HTPB |
| type | stage |
| stageno | Second |
| name | SR-119 |
| engines | 1 Solid |
| thrust | 1223 kN |
| SI | 308 isp |
| burntime | 61 seconds |
| fuel | HTPB |
| type | stage |
| stageno | Third |
| name | SR-120 |
| engines | 1 Solid |
| thrust | 289 kN |
| SI | 300 isp |
| burntime | 72 seconds |
| fuel | NEPE |
| type | stage |
| stageno | Fourth |
| name | Super-HAPS |
| engines | 12 MR-107K |
| fuel | Hydrazine |
| :: |
|name = Minotaur III |function = Heavy suborbital launch system |manufacturer = Orbital Sciences |country-origin = United States |stages = Four |capacities = |location = 5000km S/O |kilos = 3000 kg }} |status = Canceled |sites = Vandenberg SFB, SLC-8 PSCA, LP-1 |first = |launches = 0 |success = |stagedata = |type = stage |stageno = First |name = SR-118 |engines = 1 Solid |thrust = 2224 kN |SI = 229 isp (sea level) |burntime = 56.6 seconds |fuel = HTPB
|type = stage |stageno = Second |name = SR-119 |engines = 1 Solid |thrust = 1223 kN |SI = 308 isp |burntime = 61 seconds |fuel = HTPB
|type = stage |stageno = Third |name = SR-120 |engines = 1 Solid |thrust = 289 kN |SI = 300 isp |burntime = 72 seconds |fuel = NEPE
|type = stage |stageno = Fourth |name = Super-HAPS |engines = 12 MR-107K |thrust = |burntime = |fuel = 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. The Minotaur III was to be capable of launching 3000 kg of payload 5000 km downrange. 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.
Description
Minotaur III was planned to be a four-stage launch vehicle, essentially made up of a Peacekeeper missile with a Super-HAPS fourth stage, along with the Orbital-designed avionics package featured on Minotaur rockets. The first stage would have been an SR118 motor burning for 56.6 seconds, followed by the SR119 second stage motor burning for 61 seconds. The first and second stages would have average thrusts of 2224 kN and 1223 kN, respectively. The third stage S120 motor would then burn with an average thrust of 289 kN for 72 seconds, sending the payload and Super-HAPS on their final suborbital trajectory. The first three stages would feature thrust vector control to maneuver and steer the rocket.
Super-HAPS would then be used for final payload maneuvering and guidance, allowing Minotaur to provide high precision for the payload's landing or re-entry location. Super-HAPS would have been a larger and more capable variant of the monopropellant Hydrazine Auxiliary Propulsion System (HAPS), which was developed as a final maneuvering stage for the Pegasus rocket and later flown on the Minotaur I and Minotaur IV rockets. HAPS features three MR-107K thrusters, whereas Super-HAPS would have had 12.
The Minotaur III has never flown, and as of 2024, the vehicle is no longer mentioned in Minotaur-related documents and is most likely canceled. Its role was filled by the similar Minotaur IV Lite, which sports a larger fairing and no fourth stage and can send 3000 kg of payload (the same as Minotaur III) 1600 km further downrange. The Minotaur II is also available for smaller payloads, such as intercept test targets.
References
References
- Northrop Grumman. (2020-09-10). "Minotaur IV, V, VI User's Guide".
- Blau, Patrick. (2017-02-02). "Minotaur V Launch Vehicle".
- Krebs, Gunter. "Minotaur-3 (OSP-2 Peacekeepr TLV)". Gunter's Space Page.
- Krebs, Gunter. "Minotaur-3/-4/-5 (OSP-2 Peacekeeper SLV)". Gunter's Space Page.
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