Sea Launch User's Guide

7.2 Electrical Interfaces
Overview
Characteristics of the electrical interfaces are covered in the following
sections, including
• Hard-line link (umbilical).
• Radio frequency link.
• External communication.
• In-flight interfaces.
• Electrical power.
Spacecraft/adapter
in-flight electrical
disconnects
The launch vehicle adapter standard configuration accommodates two
MIL-C-26482 series connectors (61 pins) or two MIL-C-81703 series
connectors (37 pins). The spacecraft contractor should procure both
halves and provide the mating half to the launch vehicle for installation
on the adapter. Additional required connectors can be accommodated and
will be negotiated on a case-by-case basis.
Hard-line link
(umbilical)
Spacecraft hard-line link electrical interconnections between the
spacecraft/adapter in-flight disconnects and the spacecraft electrical
ground support equipment are provided by two functionally similar but
physically separate umbilical cable paths:
• Interface skirt.
• T-0.
Both umbilical paths are available during integration check out and
during transit to the launch site.
• At approximately L-8 hr the interface skirt umbilical is
disconnected.
• The T-0 umbilical remains connected until liftoff.
Table 7-1 and figure 7-6 depict umbilical configuration during spacecraft
encapsulation, integrated launch vehicle integration, transit phase, and
on-pad operations.
REV B D688-10009-1 7-7