Contents

Minotaur IV

Minotaur IV

Launch of the first Minotaur IV Lite
Function	Expendable launch system
Manufacturer	Northrop Grumman Boeing Lockheed Martin Denver Aerospace
Cost per launch	$50 million [1]
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 200 km 28.5° LEO
Mass	IV: 1,591 kg (3,508 lb) IV+: 1,837 kg (4,050 lb)[2]
Payload to 6600km S/O
Mass	IV Lite: 3,000 kilograms (6,600 lb)[2]
Associated rockets
Family	Minotaur
Derivative work	Minotaur V
Launch history
Status	Active
Launch sites	Vandenberg SFB, SLC-8 MARS, LP-0B PSCA, LP-1 CCSFS, SLC-46
Total launches	7
Success(es)	7
First flight	22 April 2010
Last flight	15 July 2020
First stage – SR-118
Powered by	1Solid
Maximum thrust	2,224 kilonewtons (500,000 lbf)[2]
Specific impulse	229 s (2.25 km/s) (sea level)[3]
Burn time	56.6 seconds
Propellant	HTPB
Second stage – SR-119
Powered by	1Solid
Maximum thrust	1,223 kilonewtons (275,000 lbf)[2]
Specific impulse	308 s (3.02 km/s)[3]
Burn time	61 seconds
Propellant	HTPB
Third stage – SR-120
Powered by	1Solid
Maximum thrust	289 kilonewtons (65,000 lbf)[2]
Specific impulse	300 s (2.9 km/s)[3]
Burn time	72 seconds
Propellant	NEPE
Fourth stage (Minotaur IV) – Orion 38
Powered by	1Solid
Maximum thrust	32.2 kilonewtons (7,200 lbf)
Specific impulse	288 s (2.82 km/s)
Burn time	67.7 seconds
Propellant	HTPB
Fourth stage (Minotaur IV+) – Star 48BV
Powered by	1Solid
Maximum thrust	68.6 kilonewtons (15,400 lbf) (average)
Specific impulse	288 s (2.82 km/s)
Burn time	84.1 seconds
Propellant	HTPB
[edit on Wikidata]

Minotaur IV, also known as Peacekeeper SLV and OSP-2 PK is an active expendable launch system derived from the LGM-118 Peacekeeper ICBM. It is operated by Northrop Grumman Space Systems, and made its maiden flight on 22 April 2010, carrying the HTV-2a Hypersonic Test Vehicle.^[4][5][6] The first orbital launch occurred on 26 September 2010 with the SBSS satellite for the United States Air Force.

The Minotaur IV vehicle consists of four stages and is capable of placing 1,591 kilograms (3,508 lb) of payload into a low Earth orbit (LEO).^[2][7] 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 48BV instead. A three-stage configuration (no Orion 38), designated the Minotaur IV Lite, is available for suborbital trajectories. The Minotaur IV has also been flown with multiple upper stages. A five-stage derivative, the Minotaur V, made its maiden flight on 7 September 2013.

Minotaur IV launches are conducted from SLC-8atVandenberg Space Force Base, LP-0B at the Mid-Atlantic Regional Spaceport, SLC-46atCape Canaveral Space Force Station and Pacific Spaceport Complex – Alaska Pad 1 of the Pacific Spaceport Complex – Alaska (PSCA).

Description[edit]

The Minotaur IV (and the overall Minotaur rocket family) was developed by Orbital Sciences (now owned by Northrop Grumman) as part of the United States Air Force's Orbital Suborbital Program.^[7] There are three variants available: Minotaur IV, IV+, and IV Lite. Minotaur IV and IV+ are used for low Earth orbit missions, while Minotaur IV Lite is intended for suborbital launches, such as testing prototype hypersonic vehicles. The separate Minotaur V is also available, consisting of a Minotaur IV+ with an added fifth stage for high-energy trajectories such as geostationary transfer orbitortrans-lunar injection.

The Minotaur IV family is derived from the LGM-118 Peacekeeper intercontinental ballistic missile (ICBM), deployed from 1985 until 2005. The Minotaur IV family utilizes decommissioned Peacekeeper solid rocket motors, which compose the first three stages in all Minotaur IV rockets and derivatives. This relatively simple architecture allows Minotaur to be launched from essentially anywhere in the US through the use of mobile launch facilities - although this capability has never been needed.^[2] Because of its use of decommissioned ICBM components, Minotaur IV can only be used to launch US government missions.

Minotaur IV[edit]

The standard Minotaur IV rocket is composed of four stages. The first stage SR118 motor provides 2,224 kilonewtons (500,000 lb_f) of thrust during its 56.6-second burn, followed immediately after by stage separation and second-stage ignition. The second stage, powered by an SR119 motor, burns for 61 seconds and provides an average thrust of 1,223 kilonewtons (275,000 lb_f). The third stage then burns for 72 seconds, with an average thrust of 289 kilonewtons (65,000 lb_f). The initial three stages all have thrust vector control, allowing them to steer the rocket downrange by gimballing the motor nozzles. The second and third stages also feature extendable nozzles, allowing for improved performance in the upper portions of Earth's atmosphere as well as the vacuum of space.

The fourth stage of the Minotaur IV is the Orion 38 motor, which is also used in the Minotaur-C, Minotaur I, Pegasus, and Ground-Based Interceptor rockets. This motor performs the final orbital insertion burn for the payload. Like the first three stages, the Orion 38 also features thrust vectoring, with a 5-degree range of motion.^[2]

On one occasion, for the ORS-5 mission, Minotaur IV was outfitted with a second Orion 38 motor to allow the payload to be inserted into an equatorial orbit. In addition, another Minotaur IV mission featured a Hydrazine Auxiliary Propulsion System (HAPS) for additional orbital maneuvering capability. The HAPS was developed for the Pegasus rocket to fine-tune the payload's orbit since solid motors are not capable of fine adjustments.

Minotaur IV+[edit]

The Minotaur IV+ is a higher-performance variant of the Minotaur IV. The first three stages are identical, but the Orion 38 fourth stage is replaced with a Star 48BV motor. The Star motor features more propellant than the Orion motor, allowing the rocket to carry roughly 200 kg (440 lb) of extra payload to low-Earth orbit, or can allow for payloads to be sent to elliptical orbits. The Star 48BV burns for 85.2 seconds with an average thrust of 68.63 kilonewtons (15,430 lb_f) and also features thrust vectoring, which is uncommon for Star 48 motors.^[2] The Star 48 motor has also seen use on the Atlas V, Delta IV, and Space Shuttle, alongside over 70 missions on the Delta II.

Minotaur IV+ was further evolved to create the Minotaur V rocket, which adds an extra Star 37FM stage to the vehicle for improved high-energy performance. This configuration has only flown once as of 2024 and is not scheduled for any further launches. In addition, the more powerful Minotaur VI and Minotaur VI+ concepts were based on the Minotaur IV+, featuring an additional SR118 motor as the first stage to improve vehicle performance. However, neither Minotaur VI variant has flown and no flights are scheduled.

Minotaur IV Lite[edit]

The Minotaur IV Lite is a suborbital configuration of Minotaur IV. It features the same first three stages as the standard variant but lacks a fourth stage. The IV Lite is intended for suborbital missions, allowing government customers to test new technologies like hypersonic aircraft or missile interception. As of May 2024, the Minotaur IV Lite has only flown twice, both times in support of the HTV-2 program.

This variant is almost identical to the unflown Minotaur III rocket, which was also intended to perform suborbital missions.

Launch history[edit]

Planned launches[edit]

STP-S26[edit]

The third Minotaur IV launch, which was also known as STP-S26, deployed eight payloads. It was the 29th small launch vehicle mission in STP's 49-year history of flying DoD space experiments,^[16] STP-S26 was intended to extend previous standard interface development efforts, implementing a number of capabilities aimed at enabling responsive access to space for small experimental satellites and payloads. STP-S96 launched at 01:25 UTC on 20 November 2019 from the Kodiak Launch Complex. The launch facility contractor was Alaska Aerospace Corporation (AAC). The payloads were released in a 650 kilometres (400 mi) orbit, before the HAPS upper stage was demonstrated by deploying two ballast payloads into a 1,200 kilometres (750 mi) orbit.

The primary objective of the STP-S26 launch was to deploy STPSAT-2 (USA-287), whilst demonstrating the ability of the Minotaur IV to carry additional payloads, by deploying FASTSAT, FASTRAC, RAX, O/OREOS and FalconSat-5. A Hydrazine Auxiliary Propulsion System upper stage was flown aboard the Minotaur to demonstrate its ability to deploy payloads to multiple orbits, however only mass simulators were deployed after the HAPS burn.

The launch marked the first flight of an STP-SIV (Standard Interface Vehicle) satellite, the first use of the Multi Mission Satellite Operations Center Ground System Architecture (MMSOC GSA), the first flight of the Minotaur IV's Multi-payload Adapter (MPA), the first use of a HAPS to obtain multiple orbits on a Minotaur IV flight, the first Minotaur launch from Kodiak Launch Complex (KLC), and the first deployment of CubeSats from a Minotaur IV via Poly-PicoSatellite Orbital Deployers (P-Pods).^[16]

See also[edit]

• Comparison of orbital launchers families
• Comparison of orbital launch systems

References[edit]

^ ^{a b} Schaub, Michael B.; Schwartz, Patrick C. "Launches". Mission Set Database. NASA/Honeywell-TSI. Archived from the original on 20 March 2009. Retrieved 23 April 2010. This article incorporates text from this source, which is in the public domain.

^ "NROL-129 Launch Press Kit" (PDF). NRO. Retrieved 9 July 2020. This article incorporates text from this source, which is in the public domain.

External links[edit]

• FASTRAC Ready To Go Into Space
• Alaskan Aerospace Corp official website