Minotaur II

Minotaur II

Minotaur II launch from Vandenberg
Function	Suborbital launch system
Manufacturer	Orbital Sciences (original); Northrop Grumman (current)
Country of origin	United States
Size
Height	19.21 metres (63.0 ft)
Diameter	1.67 metres (5 ft 6 in)
Mass	36,200 kilograms (79,800 lb)
Stages	2 or 3
Capacity
Payload to 8000km S/O
Mass	400 kilograms (880 lb)
Launch history
Status	Active
Launch sites	Vandenberg LF-06 Vandenberg TP-01
Total launches	9
Success(es)	8
First flight	28 May 2000
Last flight	7 July 2022
First stage – M55E1
Powered by	1Solid
Maximum thrust	935 kilonewtons (210,000 lbf)
Propellant	Solid
Second stage – SR19AJ1
Powered by	1Solid
Maximum thrust	268 kilonewtons (60,000 lbf)
Propellant	Solid
Third stage (Baseline) – M57A1
Powered by	1Solid
Propellant	Solid
Third stage (Minotaur II+) – SR-73-AJ
Powered by	1Solid
Propellant	Solid
Third stage (Heavy) – Orion 50XL
Powered by	1Solid
Maximum thrust	118.2 kilonewtons (26,600 lbf)
Burn time	74 seconds
Propellant	Solid
[edit on Wikidata]

Minotaur II rockets consist of the M55A1 first stage and SR19AJ1 second stage of a decommissioned Minuteman missile. The third stage varies depending on the configuration required for the payload: a Minuteman II M57A1 stage is used on the baseline configuration, whilst the Minotaur II+ uses an SR-73-AJ. The Minotaur II Lite is a two-stage configuration, without a third stage. A heavy configuration is also available, with an Orion 50XL third stage, as used on the Minotaur I. The baseline configuration can propel a 400 kilograms (880 lb) payload 4,000 kilometres (2,500 mi) downrange, whilst the heavy configuration can place 1,400 kilograms (3,100 lb) onto an 8,000-kilometre (5,000 mi) trajectory.