Orbital Minotaur VI - Manual (Page 102)

Minotaur IV • V • VI User’s Guide Section 8.0 – Optional Enhanced Capabilities
8.10. Payload Isolation System
Orbital offers a flight proven payload isolation system as a non-standard service. The Softride for Small
Satellites (SRSS) was developed by Air Force Research Laboratory (AFRL) and CSA Engineering. It has
successfully flown on numerous Minotaur missions. The typical configuration is shown in Figure 8.10-1.
This mechanical isolation system has demonstrated the capability to significantly alleviate the transient
dynamic loads that occur during flight. The isolation system can provide relief to both the overall payload
center of gravity loads and component or subsystem responses. Typically the system will reduce transient
loads to approximately 25% of the level they would be without the system. The exact results will vary for
each particular spacecraft and with location on the spacecraft. Generally, a beneficial reduction in shock
and vibration will also be provided. The isolation system does impact overall vehicle performance by
approximately 9 to 18 kg (20 to 40 lb) and the available payload dynamic envelope by up to 5.08 cm
(2.0 in.) axially and up to 2.54 cm (1.0 in.) laterally.
Figure 8.10-1. Minotaur Soft Ride Significantly Attenuates Peak LV Dynamic Environments
8.11. Orbital Debris Mitigation
For each mission, Orbital evaluates the orbit lifetime of all stages and hardware that reach Earth orbit. In
the event that Minotaur hardware is left in an orbit that lasts for 25 years or longer, this enhancement is
required to properly dispose and mitigate causality expectations of the hardware in accordance with AFI
91-217. Figure 8.11-1 shows the altitudes where
Low Earth Orbits last for more than 25 years. For
this enhancement, Orbital optimizes the orbital
debris mitigation system to the specific mission
requirements. For example, in some cases it
might be more efficient to raise the final stage to
an orbit in the LEO Disposal region. In other
cases it would be best to lower the final stage to
an orbit where natural forces can return the
hardware to the Earth’s atmosphere within 25
years. In some cases, deployment of a solar sail
or tether may be required. Orbital will determine
the optimal solution on a mission specific basis.
Figure 8.11-1. Operational and Disposal LEOs
Release 2.0 June 2013 87