|Function||Expendable launch system|
|Country of origin||United States|
|Launch sites||SLC-8, Vandenberg AFB
|First Stage - SR-118|
|Thrust||1,607 kilonewtons (361,000 lbf)|
|Burn time||83 seconds|
|Second Stage - SR-119|
|Thrust||1,365 kilonewtons (307,000 lbf)|
|Burn time||54 seconds|
|Third Stage - SR-120|
|Thrust||329 kilonewtons (74,000 lbf)|
|Burn time||62 seconds|
|Fourth Stage - Star-48V|
|Thrust||64 kilonewtons (14,000 lbf)|
|Burn time||84 seconds|
|Fifth Stage (Baseline) - Star-37FM|
|Thrust||47.26 kilonewtons (10,620 lbf)|
|Burn time||63 seconds|
|Fifth Stage (Optional) - Star-37FMV|
The Minotaur V is an American expendable launch system derived from the Minotaur IV, itself a derivative of the Peacekeeper. It is being developed by Orbital Sciences Corporation, and is scheduled to make its maiden flight in 2013 carrying the LADEE spacecraft for NASA.
The Minotaur V is a five stage vehicle, and is designed to place up to 630 kilograms (1,400 lb) of payload into a geosynchronous transfer orbit, or 437 kilograms (960 lb) on a trans-lunar trajectory. 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. The Star-37FMV upper stage is heavier, reducing payload capacity, but is more maneuverable.
Space Launch Complex 8 at the Vandenberg Air Force Base, Pad 0B at the Mid-Atlantic Regional Spaceport (MARS), and Pad 1 of the Kodiak Launch Complex are all capable of accommodating the Minotaur V, however as of 2013, no launches are scheduled from anywhere except at MARS.
- "Lunar Atmosphere and Dust Environment Explorer (LADEE) Mission website". NASA.
- "Fact Sheet". Minotaur V. Orbital Sciences Corporation. Retrieved 2013-01-22.
- Krebs, Gunter. "Minotaur-3/-4/-5 (OSP-2 Peacekeeper SLV)". Gunter's Space Page. Retrieved 2013-01-22.
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