Orbital Minotaur IV User Manual

FACT SHEET

Minotaur IV

Space Launch Vehicle

QUICK FACTS

System Features

• Full spacecraft integration support,
including mission management,
spacecraft interface support (power,
telemetry, sequencing, attitude
control, and deployment), through
launch operations and post-launch
performance evaluation

• Flexible design enables multiple
mission tailoring options

• Cost effective space launch

• Responsive launch solutions available

• Mission success is ensured by mature
systems and processes

- Orbital’s rigorous mission assurance

program

- Full government insight and

independent assessment

• Multiple spaceport launch capability
(California, Florida, Alaska, Mid­Atlantic) using portable ground support
equipment

Overview

The ight proven Minotaur IV Space Launch Vehicle (SLV) provides an extremely cost-effective and
capable space solution for U.S. Government-sponsored spacecraft. It builds on a long background
of dependable launch systems with over 50 ights of each core stage. The combination of three
government-furnished solid rocket stages, a commercial solid rocket upper stage, and Orbital’s ight­proven systems and processes provide an unmatched mix of value and performance. The integration
of government motors with commercial boosters and state-of-the-art hardware is one of Orbital’s
unique strengths from experience spanning several decades.

For the Minotaur IV, the standard Minotaur-family avionics, ight software, and subsystems are
integrated into a Guidance Control Assembly (GCA) which also incorporates the Stage 4 solid motor.
The baseline Stage 4 motor is the same Orion 38 design used on Minotaur I, and other Orbital launch
vehicles. An optional STA R™48BV motor has been ight demonstrated and is available for additional
performance in the Minotaur IV+ conguration.

The Minotaur family of launch vehicles are provided via the Orbital/Suborbital Program (OSP)
managed by the U.S. Air Force Space and Missile Systems Center (SMC), Space Development and Test
Directorate (SMC/SD) Launch Systems Division (SMC/SDL) located at Kirtland Air Force Base, New
Mexico.

Separation Systems

Payload Interface

▲Payload Adapter

Fittings

Stage 4 Motors

TM

▲STAR

Additional payload accomodation details can
be found in the Minotaur IV Users Guide.

48

▲Payload

Cones

▲Orion 38

Minotaur IV

Performance

• System performance assured from extensive booster motor ight history of
more than 50 ights each

• Typical orbit accuracy better than ±5 km insertion apse, ±25 km non-insertion
apse, and ±0.1 deg inclination (3-sigma values)

• Optional enhanced insertion accuracy available

• Cold gas at titude control system readily accommodates a variety of spacecraft
mission requirements, including precise separation pointing and post-boost
maneuvers

• Minotaur IV with optional STAR™ 48BV Stage 4 provides up to 225 kg increased
performance to LEO and support for HEO missions

Payload Accommodations

• Standard 2.34 m (92 in) diameter spacecraft fairing

• Mission-specic fairing access doors for spacecraft support

• Spacecraft and fairing assembly integrated independently from launch vehicle
stages

• Well-dened launch environments derived from extensive ight data

• Temperature, humidity, and cleanliness control through lift-off

• Standard 986 mm (38.81 in) diameter bolted interface with optional spacecraft
support options

- Single and multiple spacecraft adaptors

- Various ight-proven spacecraft separation systems available, including low-

shock designs

• Multiple Payload Adapter Fitting (MPAF) option

• Hydrazine upper stage for multiple orbit altitude capabilities or increased orbital

insertion accuracy

160 0

*

140 0

NOTE: Pay load Mass in cludes

1200

1000

Payload (kg)

800

600

* Detai led Anal ysis Neede d for

Missio ns to These Alt itudes

400

200 400 600 800 1000 1200 1400 1600 1800

Orbit Altitude (km)

Ø0.48 m

(19.2 in)

0.87 m

(34.5 in)

1.52 m

(60.0 in)

2.87 m

(113.3 in)

Ø38.81 in In terface

(No Sep System)

Fairin g Sep Plan e

Adapte r Cone, Sep aration
System a nd Other Miss ion­Speci c Hardware

*

Ø1.33 m

(Ø52.5 in)

Ø2.05 m

(Ø80.9 in)

CCAS 28.5°
WFF 43°

°

VAFB 72

°

Kodiak 63.4
VAFB Sun -Synch

For technical details or questions
please contact Orbital at:

[e-mail]

Orbital Sciences Corporation

45101 Warp Drive

©2014 Orbita l Sciences Corporatio n BR06005_2429

•

Dulles, Virginia 20166

Copies of the Minotaur User's Guide
can be downloaded from:

www.orbital.com

•

www.orbital.com

Standard Fairing

Additional information should be
from the USAF OSP Ofce

USAF SMC Space Development
and Test Directorate (SMC/SD)

Launch Systems Division (SMC/SDL)
Kirtland AFB, NM 87117-5778
[phone] [phone]

obtained