Orbital Minotaur I - Manual (Page 21)

Minotaur I User’s Guide Section 2.0 – Minotaur I Configurations
The TDRSS then relays the telemetry to the ground where it is routed to the Launch Control Room for
real-time telemetry updates. Reference Enhancements Section 8.8 for further details on this Over the
Horizon Telemetry option.
Minotaur telemetry is subject to the provisions of the Strategic Arms Reduction Treaty (START). START
treaty provisions require that certain Minotaur I telemetry be unencrypted and provided to the START
treaty office for dissemination to the signatories of the treaty.
2.3.3. Payload Interface
Minotaur provides for a standard non-separating payload interface, with the option of adding an Orbital-
provided payload separation system. Orbital will provide all flight hardware and integration services
necessary to attach non-separating and separating payloads to the Minotaur launch vehicle. Additional
mechanical interface diameters and separation system configurations can readily be provided as an
enhanced option as described in Section 5.0. Further detail on payload electrical, mechanical and launch
support equipment interfaces are detailed in Section 5.0.
Because of its design flexibility, Minotaur can accommodate and has flown missions with multiple
spacecraft. This capability, described in more detail in Section 5.0 of this User’s Guide, permits two or
more smaller payloads to share the cost of a Minotaur I launch, resulting in a lower launch cost for each
as compared to other launch options. Furthermore, Orbital can accommodate small payloads when there
is excess payload and/or mass capability.
2.3.4. Payload Fairing
The baseline Minotaur I 50” fairing, shown in
Figure 2.3.4-1, is identical to the Pegasus fairing
design and has been successfully deployed in
over 40 Pegasus and Minotaur I missions. Due to
differences in vehicle loads and environments, the
Minotaur I implementation allows for a larger
payload envelope than Pegasus. The Minotaur I
payload fairing consists of two composite shell
halves, a nose cap integral to one shell half, and a
separation system. Each shell half is composed of
a cylinder and ogive sections.
Options for payload access doors and enhanced
cleanliness are available. A larger 61” diameter
fairing is also available. Further details on both
fairings are included in Section 5.1.
Figure 2.3.4-1. Minotaur I 50” Fairing and
Handling Fixtures
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