Orbital Minotaur I - Manual (Page 50)

Minotaur I User’s Guide Section 5.0 – Payload Interfaces
are within specified limits presented in Section 5.4.1. Separation velocities are usually optimized to
provide the SV with the lowest separation velocity while ensuring recontact does not occur between the
SV and the Minotaur upper stage after separation. The spacecraft is deployed by matched push-off
springs with sufficient energy to produce the required relative separation velocity to prevent re-contact
with the LV. If non-standard separation velocities are needed, alternative springs may be substituted on a
mission-specific basis as a non-standard service. SV separation dynamics are highly dependent on the
mass properties of the SV and the particular separation system utilized. Typical separation velocity is 0.6
to 0.9 m/sec (2 to 3 ft/sec). As a standard service, Orbital performs a mission-specific tip-off and
separation analyses for each SV.
5.2.5.1. Orbital 38” Separation System
The flight proven Orbital 38” separation system, Figure 5.2.5.1-1, is composed of two rings connected by
a marmon clamp band which is separated by redundant bolt cutters. This system has flown successfully
on over twenty Orbital launch vehicle missions to date. The weight of hardware separated with the SV is
approximately 4.0 kg (8.7 lbm). Orbital-provided attachment bolts to this interface can be inserted from
either the launch vehicle or the SV side of the interface via the through-holes in the separation system
flange (NAS630xU, fastener length based on SV flange thickness).
In addition to the 38” configuration, Orbital has flight qualified 23” and 17” separation systems. Each of
these three systems is based on the marmon clamp band design.
Table 5.2.5-1. Minotaur I Separation System Options
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