Minotaur V

Minotaur V

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	1 Solid
Maximum thrust	2,200 kN (490,000 lbf)
Burn time	83 seconds
Propellant	Solid
Second stage – SR-119
Powered by	1 Solid
Maximum thrust	1,365 kilonewtons (307,000 lbf)
Burn time	54 seconds
Propellant	Solid
Third stage – SR-120
Powered by	1 Solid
Maximum thrust	329 kilonewtons (74,000 lbf)
Burn time	62 seconds
Propellant	Solid
Fourth stage – Star-48BV
Powered by	1 Solid
Maximum thrust	64 kilonewtons (14,000 lbf)
Burn time	84 seconds
Propellant	Solid
Fifth stage (Baseline) – Star-37FM
Powered by	1 Solid
Maximum thrust	47.26 kilonewtons (10,620 lbf)
Burn time	63 seconds
Propellant	Solid
Fifth stage (Optional) – Star-37FMV
Powered by	1 Solid
Propellant	Solid
[edit on Wikidata]

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 April 2024.