Minotaur IV

Minotaur IV
Function	Expendable launch system
Manufacturer	Orbital Sciences
Country of origin	United States
Size
Height	23.88 metres (78.3 ft)
Diameter	2.34 metres (7 ft 8 in)
Mass	86,300 kg
Stages	4
Capacity
Payload to LEO
Mass	1735 kg (28.5 deg, 185 km)
Associated rockets
Family	Minotaur
Derivative work	Minotaur V
Launch history
Status	Development
Launch sites	SLC-8, Vandenberg AFB; LP-0B, MARS; LP-1, Kodiak
Total launches	0
First flight	April 2010 (planned)
First stage – SR-118
Powered by	1 Solid
Maximum thrust	2,200 kilonewtons (490,000 lbf)
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 (Baseline) – Orion-38
Powered by	1 Solid
Maximum thrust	32.2 kilonewtons (7,200 lbf)
Burn time	67.7 seconds
Propellant	Solid
Fourth stage (Optional) – Star-48V
Powered by	1 Solid
Maximum thrust	68.6 kilonewtons (15,400 lbf)
Burn time	84.1 seconds
Propellant	Solid
	[edit on Wikidata]

The Minotaur IV, also known as Peacekeeper SLV and OSP-2 PK is an American expendable launch system derived from the Peacekeeper missile. It is being developed by Orbital Sciences Corporation, and was scheduled to make its maiden flight in October 2009, with the SBSS satellite for the United States Air Force. Currently its maiden flight is scheduled to be a suborbital launch of a Hypersonic Test Vehicle HTV-2, scheduled for April 2010.

The Minotaur IV is a four stage vehicle, capable of placing 1,735 kilograms (3,825 lb) of payload into a Low Earth orbit (LEO). It uses the first three stages of the Peacekeeper missile, combined with a new upper stage. On the baseline version, the fourth stage is an Orion-38, however a higher performance variant, designated Minotaur IV+, uses a Star-48V instead. A three stage configuration (no Orion-38), designated the Minotaur IV Lite, is available for Suborbital trajectories. A five stage derivative, the Minotaur V, is also under development.

Minotaur IV launches will be conducted from SLC-8 at Vandenberg Air Force Base, LP-0B at the Mid-Atlantic Regional Spaceport, and Pad 1 of the Kodiak Launch Complex.

Launches

Date/Time (UTC)	Variant	Launch Site	Payload	Trajectory	Remarks
2nd Q 2010	Minotaur IV Lite	Vandenberg SLC-8	HTV-2a	Suborbital	Hypersonic Test Vehicle
3rd Q 2010	Minotaur IV	Vandenberg SLC-8	SBSS	LEO
3rd Q 2010	Minotaur IV	Kodiak LP-1	STP S26 FASTRAC-A FASTRAC-B FalconSat-5 FASTSAT O/OREOS RAX	LEO	Includes a Hydrazine Auxiliary Propulsion System (HAPS) to take the vehicle to a secondary orbit
4rd Q 2010	Minotaur IV+	Kodiak LP-1	TacSat-4	LEO	First Minotaur IV+ launch
1st Q 2011	Minotaur IV Lite	Vandenberg SLC-8	HTV-2b	Suborbital
4th Q 2011	Minotaur IV Lite	Vandenberg SLC-8	CSM	Suborbital
3rd Q 2012	Minotaur IV	Vandenberg SLC-8	TacSat-5	LEO	Might launch on a Minotaur I

References

Krebs, Gunter. "Minotaur-3/-4/-5 (OSP-2 Peacekeeper SLV)". Gunter's Space Page. Retrieved 2009-03-04.
"Fact Sheet" (PDF). Minotaur IV. Orbital Sciences Corporation. Retrieved 2009-03-04.

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v t e Orbital launch systems
List of orbital launch systems Comparison of orbital launch systems
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v t e Orbital launch systems developed in the United States
Active	Atlas V**^†† Electron Falcon 9 Block 5 Falcon Heavy Firefly Alpha Minotaur I IV V C Pegasus XL SLS Block 1 Vulcan Centaur
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