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 (80.6 ft)[1]
Diameter	2.34 m (7 ft 8 in)[1]
Mass	89,373 kg (197,034 lb)[1]
Stages	5
Capacity
Payload to GTO
Mass	532 kg (1,173 lb)
Payload to TLI
Mass	342 kg (754 lb)
Associated rockets
Family	Minotaur
Launch history
Status	Active, no planned launches
Launch sites	Wallops Island, LP-0B
Total launches	1
Success(es)	1
First flight	7 September 2013
First stage – SR-118
Maximum thrust	2,200 kN (490,000 lbf)
Burn time	83 seconds
Propellant	HTPB
Second stage – SR-119
Maximum thrust	1,365 kN (307,000 lbf)
Burn time	54 seconds
Propellant	HTPB
Third stage – SR-120
Maximum thrust	329 kN (74,000 lbf)
Burn time	62 seconds
Propellant	NEPE
Fourth stage – Star-48BV
Maximum thrust	64 kN (14,000 lbf)
Burn time	84 seconds
Propellant	HTPB
Fifth stage – Star-37FM
Maximum thrust	47.26 kN (10,620 lbf)
Burn time	63 seconds
[edit on Wikidata]

Minotaur V is an American expendable launch system derived from the Minotaur IV, itself a derivative of the LGM-118 Peacekeeper, an intercontinental ballistic missile. It 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.^[2] While Minotaur V is still likely active and available to fly, no further flights are scheduled as of May 2024.