Orbital Antares - Manual (Page 60)

Antares
®
OSP-3
User’s Guide
Section 6.0
– Mission Integration
Release 1.1 July 2013 49
6.3.5.2. Mission ICD Verification Documentation
Orbital conducts a rigorous verification program to ensure all requirements on both sides of the launch
vehicle-to-payload interface have been successfully fulfilled. Like the customer-provided verification data
discussed in Section 6.3.4.6, Orbital will provide the customer with data for all interfaces that are the re-
sponsibility of the launch vehicle to verify. This documentation will be used as part of the team effort to
complete a thorough verification that all ICD requirements have been met.
6.3.5.3. Preliminary Mission Analysis (PMA)
Orbital performs a PMA to determine the compatibility of the payload with the Antares launch vehicle and
to support development of the mission requirements such as launch vehicle trajectory analysis, perfor-
mance capability, accuracy estimates and preliminary mission sequencing.
6.3.5.4. Coupled Loads Analyses (CLA)
Orbital has developed and validated finite element structural models of the Antares vehicle for use in
CLAs with Antares payloads. Orbital will incorporate the customer-provided payload model into the An-
tares finite element model and perform a preliminary CLA to determine the maximum responses of the
entire integrated stack under transient loads. Once a test validated spacecraft model has been delivered
to Orbital, a final CLA load cycle is completed. Through close coordination between the customer and the
Antares Program, interim results can be made available to support the customer
’s schedule critical
needs.
6.3.5.5. Radio Frequency (RF) Link Analysis
Orbital will perform an RF link analysis for each mission to ensure that a sufficient RF link margin exists
for the telemetry system and for the flight termination system.
6.3.5.6. Final Mission Analysis (FMA)
The FMA presents a detailed trajectory analysis for the payload using final contractual mass property in-
puts. The FMA includes results from a Six Degrees of Freedom (6DOF) simulation; a separation analysis
for the stage and payload separation events; and results of a Monte-Carlo analysis defining dispersions
for the orbit insertion parameters.
6.3.5.7. Integrated Launch Site Procedures
For each mission, Orbital prepares integrated procedures for various operations that involve the payload
at the processing facility and launch site. These include, but are not limited to: payload mate to the An-
tares launch vehicle; fairing encapsulation; flight simulations; final vehicle closeouts, and transport of the
integrated launch vehicle/payload to the launch pad. Once customer inputs are received, Orbital will de-
velop draft procedures for review and comment. Once concurrence is reached, final procedures will be
released prior to use. Draft hazardous procedures must be presented to the appropriate launch site safe-
ty organization 90 days prior to use and final hazardous procedures are due 45 days prior to use.
6.3.5.8. Missile System Pre-Launch Safety Package (MSPSP) Annex
The MSPSP Annex documents launch vehicle and payload safety information including an assessment of
any hazards which may arise from mission-specific vehicle and/or payload functions, and is provided as
an annex to the baseline Antares MSPSP. The customer must provide Orbital with all safety information
pertaining to the payload. Orbital assesses the combined vehicle and payload for hazards and prepares
a report of the findings. Orbital will then forward the integrated assessment to the appropriate launch
Range for approval.