Orbital Minotaur VI - Manual (Page 71)

Minotaur IV • V • VI User’s Guide Section 5.0 – Payload Interfaces
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 payload tip-off and overall
separation velocity. Payload tip-off refers to the angular velocity imparted to the payload upon separation
due to payload CG offsets and an uneven distribution of torques and forces. Payload tip-off rates induced
by the separation systems presented are generally under 1 deg/sec per axis. Entering into the payload
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 are within specified limits presented in Section 5.4.1. Separation velocities are usually optimized to
provide the spacecraft with the lowest separation velocity while ensuring recontact does not occur
between the payload and the Minotaur upper stage after separation. The spacecraft is ejected by
matched push-off springs with sufficient energy to produce the required relative separation velocity to
prevent re-contact with the spacecraft. If non-standard separation velocities are needed, alternative
springs may be substituted on a mission-specific basis as a non-standard service. Payload separation
Figure 5.2.4.2.3-1. Dynamic Envelope for
Standard 92” Fairing and Minotaur V / VI+
Enhanced Performance Option
Figure 5.2.4.2.3-2. Dynamic Envelope for
Standard 92” Fairing and Minotaur V / VI+
Enhanced Performance Option
with Optional PAF
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