Orbital Minotaur I - Manual (Page 49)

Minotaur I User’s Guide Section 5.0 – Payload Interfaces
structure that supports the dual payload
configuration includes a 50” cylindrical section that
is configurable in height depending on payload
unique requirements. The primary payload is
mounted to the top of this DPAF structure using a
38.8” separation system. The lower payload
resides within the DPAF structure during flight
through primary payload deployment. After the
primary payload is deployed, the DPAF structure is
released using a separation system that reveals
the secondary payload. The secondary payload is
released using a 38.8” separation system at the
38.8” interface or via a smaller separation system
mounted to a payload adaptor cone. As spacecraft
have many options in separation systems that are
available to support a given mission, both primary
and secondary payload release mechanisms are
not included in this enhancement as they are
addressed in Section 8.1.
5.2.5. Optional Separation Systems
Three separation system options are offered as
flight proven enhancements for Minotaur I. All
systems are configurable to various interface
diameters and have extensive flight history. These
separation systems include the Orbital marmon
clamp band system, Planetary Systems Corp.
Motorized Lightband (MLB) System, and RUAG
low-shock marmon clamp band system. Through
this enhancement, Orbital procures the qualified
separation system hardware, conducts separation
testing and analyses, and integrates the system
onto the launch vehicle. The separation system
options are summarized in Table 5.2.5-1.
The primary separation parameters associated
with a separation system are SV tip-off and overall
separation velocity. SV tip-off refers to the angular
velocity imparted to the SV upon separation due to
SV CG offsets and an uneven distribution of
torques and forces. SV tip-off rates induced by the
separation systems presented are generally under
1 deg/sec per axis. Entering into the SV separation
phase, the launch vehicle reduces vehicle rates.
The combined tip-off rate of the separation system
and launch vehicle is generally less than 2 deg/sec
about each axis when spacecraft mass CG offsets
Figure 5.2.4.1.1-3. Five Bay Multiple Payload
Adapter Concept
Figure 5.2.4.1.2-1. DPAF Configuration
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