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[1] |
| Diameter | 2.34 m[1] |
| Mass | 89,373 kg[1] |
| Stages | Five |
| Capacity | |
| Payload to GTO | |
| Mass | 532 kg |
| Payload to TLI | |
| Mass | 342 kg |
| Associated rockets | |
| Family | Minotaur |
| Launch history | |
| Status | Active, no planned launches |
| Launch sites | SLC-8, Vandenberg SFB LP-0B, MARS LP-1, Kodiak |
| Total launches | 1 |
| Success(es) | 1 |
| First flight | 7 September 2013 |
| First stage – SR-118 | |
| Powered by | 1Solid |
| Maximum thrust | 2,200 kN (490,000 lbf) |
| Burn time | 83 seconds |
| Propellant | Solid |
| Second stage – SR-119 | |
| Powered by | 1Solid |
| Maximum thrust | 1,365 kilonewtons (307,000 lbf) |
| Burn time | 54 seconds |
| Propellant | Solid |
| Third stage – SR-120 | |
| Powered by | 1Solid |
| Maximum thrust | 329 kilonewtons (74,000 lbf) |
| Burn time | 62 seconds |
| Propellant | Solid |
| Fourth stage – Star-48BV | |
| Powered by | 1Solid |
| Maximum thrust | 64 kilonewtons (14,000 lbf) |
| Burn time | 84 seconds |
| Propellant | Solid |
| Fifth stage (Baseline) – Star-37FM | |
| Powered by | 1Solid |
| Maximum thrust | 47.26 kilonewtons (10,620 lbf) |
| Burn time | 63 seconds |
| Propellant | Solid |
| Fifth stage (Optional) – Star-37FMV | |
| Powered by | 1Solid |
| Propellant | Solid |
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.[2] While Minotaur V is still likely active and available to fly, no further flights are scheduled as of May 2024.
Minotaur V is a five-stage vehicle and is designed to place up to 630 kilograms (1,390 lb) of payload into a geosynchronous transfer orbit, or 342 kilograms (754 lb) on a trans-lunar trajectory.[3] It consists of a Minotaur IV+, with a Star-37 as a fifth stage. Two variants are available, one with a spin-stabilized Star-37FM upper stage, and the other with a Star-37FMV capable of three-axis stabilization.[3] The Star-37FMV upper stage is heavier, reducing payload capacity, but is more maneuverable.
Space Launch Complex 8 at the Vandenberg Space Force Base, Pad 0B at the Mid-Atlantic Regional Spaceport (MARS), and Pad 1 of the Kodiak Launch Complex are all capable of accommodating Minotaur V. As of 2024[update], the vehicle has only launched from MARS.[4]
The only Minotaur V occurred on 7 September 2013 at 03:27 UTC from Launch Pad 0B at the Mid-Atlantic Regional Spaceport in Virginia. The payload for the maiden flight was the LADEE lunar exoatmosphere science spacecraft (SATCAT: 39246, decay date: 18 April 2014).[5] While now separated from the LADEE spacecraft, both the fourth and fifth stages of the Minotaur V reached orbit, and became derelict satellitesinEarth orbit (SATCAT: 39248, decay date: 27 November 2013).[6]
| Flight number | Date (UTC) | Launch site | Payload | Orbit | Outcome |
|---|---|---|---|---|---|
| 1 | September 7, 2013 03:27 |
MARS LP-0B | LADEE | LTO | Success |
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Orbital launch systems developed in the United States
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| Active |
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| In development |
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| Retired |
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