Orbital Minotaur VI - Manual (Page 78)

Minotaur IV • V • VI User’s Guide Section 5.0 – Payload Interfaces
The Minotaur avionics are in close proximity to the payload inside the fairing such that radiated emissions
compatibility is paramount. Orbital places no firm radiated emissions limits on the payload other than the
prohibition against RF transmissions within the payload fairing. Prior to launch, Orbital requires review of
the payload radiated emission levels (MIL-STD-461, RE02) to verify overall launch vehicle EMI safety
margin (emission) in accordance with MIL-E-6051. Payload RF transmissions are not permitted after
fairing mate and prior to an ICD specified time after separation of the payload. An EMI/EMC analysis may
be required to ensure RF compatibility.
Payload RF transmission frequencies must be coordinated with Orbital and range officials to ensure non-
interference with Minotaur and range transmissions. Additionally, the customer must schedule all RF tests
at the integration site with Orbital in order to obtain proper range clearances and protection.
5.4.5. Payload Dynamic Frequencies
To avoid dynamic coupling of the payload modes with the natural frequency of the launch vehicle, the
spacecraft should be designed with a structural stiffness to ensure that the lateral fundamental frequency
of the spacecraft, fixed at the spacecraft interface is typically greater than 15 Hz lateral. However, this
value is significantly affected by other factors such as incorporation of a spacecraft isolation system
and/or separation system. Therefore, the final determination of compatibility must be made on a mission-
specific basis.
5.4.6. Payload Propellant Slosh
A slosh model should be provided to Orbital in either the pendulum or spring-mass format. Data on first
sloshing mode are required and data on higher order modes are desirable. Additional critical model
parameters will be established during the mission development process. The slosh model should be
provided with the payload finite element model submittals.
5.4.7. Payload-Supplied Separation Systems
If the payload employs a non-Orbital separation system, then the shock delivered to the LV interface must
not exceed the limit level characterized in Section 4.3 (Figure 4.4-2). Shock above the stated level could
require a requalification of LV components.
5.4.8. System Safety Constraints
OSP considers the safety of personnel and equipment to be of paramount importance. AFSPCM 91-710
outlines the safety design criteria for Minotaur payloads. These are compliance documents and must be
strictly followed. It is the responsibility of the customer to ensure that the payload meets all OSP, Orbital,
and range imposed safety standards.
Customers designing payloads that employ hazardous subsystems are advised to contact OSP early in
the design process to verify compliance with system safety standards.
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