Orbital Minotaur VI - Manual (Page 20)

Minotaur IV • V • VI User’s Guide Section 2.0 – Minotaur IV Configurations
austere launch sites using portable vans, typical operations occur from permanent facilities on
established ranges.
The Minotaur IV system is designed to be capable of launch from four commercial Spaceports (Alaska,
California, Florida, and Mid-Atlantic), as well as from existing U.S. Government facilities at VAFB and
CCAFS. A Launch Control Room (LCR) serves as the control center for conducting a Minotaur IV launch
and includes consoles for Orbital, range safety, and limited customer personnel. Further description of the
Launch Support Equipment is provided in Section 2.4.
2.2. Minotaur IV Launch Service
The Minotaur IV Launch Service is provided through the combined efforts of the USAF and Orbital, along
with associate contractors and commercial spaceports. The primary customer interface will be with the
USAF Space and Missile Systems Center, Space Development and Test Directorate (SD), Launch
Systems Division (SDL). Orbital is the launch vehicle provider. This integrated team will be referred to
collectively as “OSP” throughout the User’s Guide. Where necessary, interfaces that are associated with
a particular member of the team will be referred to directly (i.e., Orbital or SDL).
OSP provides all of the necessary hardware, software and services to integrate, test, and launch a
payload into its prescribed orbit. In addition, OSP will complete all the required agreements, licenses and
documentation to successfully conduct Minotaur IV operations. The Minotaur IV mission integration
process completely identifies, documents, and verifies all spacecraft and mission requirements.
2.3. Minotaur IV Launch Vehicle
The Minotaur IV baseline vehicle, shown in expanded view in Figure 2.3-1, is a four-stage, inertially
guided, all solid propellant ground launched vehicle. Conservative design margins, state-of-the-art
structural systems, a modular avionics architecture and simplified integration and test capability yield a
robust, highly reliable launch vehicle design. In addition, Minotaur IV payload accommodations and
interfaces are designed to satisfy a wide range of potential payload requirements.
2.3.1. Stage 1, 2 and 3 Booster Assemblies
The first three stages of the Minotaur IV consist of the refurbished Government Furnished Equipment
(GFE) Peacekeeper Stages 1, 2, and 3, shown in Figure 2.3.1-1. These booster assemblies are used as
provided by the Government, requiring no modification. They have extensive flight history, with over 50
launches. All three stages are solid-propellant motors and utilize a movable nozzle controlled by a Thrust
Vector Actuator (TVA) system for three-axis attitude control. The first stage provides 500,000 lbf (2224
kN) of thrust. The second stage motor has an extendable exit cone and provides an average thrust of
275,000 lbf (1223 kN). The third stage provides 65,000 lbf (289 kN) of thrust and also features an
extendable exit cone similar to Stage 2.
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