Minotaur II

Minotaur II

Minotaur II launch from Vandenberg
Function	Suborbital launch system
Manufacturer	Orbital Sciences
Country of origin	United States
Size
Stages	2 or 3
Capacity
Payload to 8000km S/O	400 kilograms (880 lb)
Launch history
Status	Active
Launch sites	Vandenberg LF-06
Total launches	8
Successes	8
First flight	28 May 2000
First stage - M55E1
Engines	1 Solid
Thrust	935 kilonewtons (210,000 lbf)
Fuel	Solid
Second stage - SR19AJ1
Engines	1 Solid
Thrust	268 kilonewtons (60,000 lbf)
Fuel	Solid
Third stage (Baseline) - M57A1
Engines	1 Solid
Fuel	Solid
Third stage (Minotaur II+) - SR-73-AJ
Engines	1 Solid
Fuel	Solid
Third stage (Heavy) - Orion 50XL
Engines	1 Solid
Thrust	118.2 kilonewtons (26,600 lbf)
Burn time	74 seconds
Fuel	Solid

The Minotaur II, also known as Chimera, Target Launch Vehicle, Minuteman II TLV or OSP TLV is an American rocket derived from the Minuteman II missile. It is a member of the Minotaur family of rockets produced by Orbital Sciences Corporation, and is used for long range suborbital launches.

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 into a 4,000 kilometres (2,500 mi) downrange, whilst the heavy configuration can place 1,400 kilograms (3,100 lb) onto a 8,000-kilometre (5,000 mi) trajectory.

Eight Minotaur IIs have been launched as of May 2009, with six flights using the baseline configuration and two using the Minotaur II+ configuration. Launches are conducted from Launch Facility 06.

Launch history

References