Minotaur V

Minotaur V
The first Minotaur V at MARS before the launch of LADEE.
FunctionExpendable launch system
ManufacturerNorthrop Grumman
Country of originUnited States
Cost per launch$46 million (2010)
Size
Height24.56 m (80.6 ft)
Diameter2.34 m (7 ft 8 in)
Mass89,373 kg (197,034 lb)
Stages5
Capacity
Payload to MTO
Mass650 kg (1,430 lb)
Payload to GTO
Mass532 kg (1,173 lb)
Payload to TLI
Mass342 kg (754 lb)
Associated rockets
FamilyMinotaur
Launch history
StatusActive, no planned launches
Launch sitesWallops Island, LP-0B
Total launches1
Success(es)1
First flight7 September 2013
First stage – SR-118
Maximum thrust2,224 kN (500,000 lbf)
Specific impulse229 s (2.25 km/s)
Burn time56.6 seconds
PropellantHTPB
Second stage – SR-119
Maximum thrust1,223 kN (275,000 lbf)
Specific impulse308 s (3.02 km/s)
Burn time61 seconds
PropellantHTPB
Third stage – SR-120
Maximum thrust289 kN (65,000 lbf)
Specific impulse300 s (2.9 km/s)
Burn time72 seconds
PropellantNEPE
Fourth stage – Star 48BV
Maximum thrust68.6 kN (15,400 lbf)
Specific impulse288 s (2.82 km/s)
Burn time84.1 seconds
PropellantHTPB
Fifth stage – Star 37FM / Star 37FMV
Maximum thrustFM: 54.8 kN (12,300 lbf)
FMV: 55.6 kN (12,500 lbf)
Specific impulseFM: 290 s (2.8 km/s)
FMV: 294 s (2.88 km/s)
Burn time62.7 seconds
PropellantHTPB

Minotaur V is an American expendable launch system derived from the Minotaur IV, itself a derivative of the retired LGM-118 Peacekeeper ICBM. Minotaur V was developed by Orbital Sciences Corporation (now absorbed into Northrop Grumman) and made its maiden, and to date only, flight on 7 September 2013 carrying the LADEE (Lunar Atmosphere and Dust Environment Explorer) spacecraft for NASA. Although Minotaur V is still offered for launch services, no further flights are scheduled as of 2025.