Orbital Minotaur I - Manual (Page 22)

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations
2.4. Launch Support Equipment
The Minotaur I LSE is designed to be readily adaptable to varying launch site configurations with minimal
unique infrastructure required. The EGSE consists of readily transportable consoles that can be housed
in various facility configurations depending on the launch site infrastructure. The EGSE is composed of
three primary functional elements: Launch Control, Vehicle Interface, and Telemetry Data Reduction. The
Launch Control and Telemetry Data Reduction consoles are located in the Launch Control Room (LCR),
or mobile launch equipment van depending on available launch site accommodations. The Vehicle
Interface consoles are located at the launch pad in a permanent structure, typically called a Launch
Equipment Vault (LEV). Fiber optic connections from the Launch Control to the Vehicle Interface consoles
are used for efficient, high bandwidth communications, eliminating the need for copper wire between
locations. The Vehicle Interface consoles provide the junction from fiber optic cables to the cables that
directly interface with the vehicle. Figure 2.4-1 depicts the functional block diagram of the LSE. All
Minotaur EGSE is compliant with the Department of Defense Instruction 8510.01, DoD Information
Assurance Certification and Accreditation Process (DIACAP). Some launch sites have a separate
Support Equipment Building (SEB) that can accommodate additional payload equipment.
The LCR serves as the control center during the launch countdown. The number of personnel that can be
accommodated is dependent on the launch site facilities. At a minimum, the LCR will accommodate
Orbital personnel controlling the vehicle, two Range Safety representatives (ground and flight safety), and
the Air Force Mission Manager. Mission-unique, customer-supplied payload consoles and equipment can
be supported in the LCR and payload equipment at the launch pad can be supported in the LEV or SEB,
if available, within the constraints of the launch site facilities. Interface to the payload through the
Minotaur I payload umbilicals provides the capability for direct monitoring of payload functions. Payload
personnel accommodations will be handled on a mission-specific basis.
All of the Mechanical Ground Support Equipment (MGSE) used to support the Minotaur integration, test
and launch is currently in use and launch demonstrated. MGSE fully supports all Minotaur configurations
and are routinely static load tested to safety factors in compliance with Orbital internal and Range
requirements.
Release 3.0 March 2014 9