Orbital Minotaur I - Manual (Page 71)

Minotaur I User’s Guide Section 7.0 – Ground and Launch Operations
7.2.1. Payload to Minotaur I Integration
The integrated launch processing activities are designed to simplify final launch processing while
providing a comprehensive verification of the payload interface. The systems integration and test
sequence is engineered to ensure all interfaces are verified.
7.2.2. Pre-Mate Interface Testing
If required, the electrical interface between Minotaur I and the payload is verified using a mission unique
Interface Verification Test (IVT) to jointly verify that the proper function of the electrical connections and
commands. These tests, customized for each mission, typically check bonding, electrical compatibility,
communications, discrete commands and any off nominal modes of the payload. For pre-mate verification
of the mechanical interface, the separation system can also be made available before final payload
preparations.
7.2.3. Payload Mating and Verification
Once the payload aft end closeouts are completed, the payload will be both mechanically and electrically
mated to the Minotaur I. Following mate, the flight vehicle is ready for the final integrated systems test,
Mission Simulation #3.
7.2.4. Final Processing and Fairing Closeout
After successful completion of Mission Simulation #3, all consumables are topped off and ordnance is
connected. Similar payload operations may occur at this time. Once consumables are topped off, final
vehicle / payload closeout is performed and the fairing is installed. The payload will coordinate with
Orbital access to the payload from payload mate until final closeout before launch.
7.2.5. Payload Propellant Loading
Payloads utilizing integral propulsion systems with propellants such as hydrazine can be loaded and
secured through coordinated OSP arrangements. This is a non-standard service.
7.3. Launch Operations
At the completion of activities at the MPF and PPF, the final phase of the Launch campaign is entered.
This begins with the stacking of the booster stages and culminates with the launch of the Minotaur I and
payload. A notional launch operations flow chart is shown in Figure 7.3-1. The L-minus dates may vary
from mission to mission depending on vehicle configuration and other range commitments. Launch
operations activities are described in more detail in the subsections to follow.
Figure 7.3-1. Minotaur I Launch Site Operations
Release 3.0 March 2014 58