Orbital Pegasus - Manual (Page 70)

Release 7.0 Apr 2010 59
Pegasus User’s Guide
Pegasus will be integrated at Vandenberg and
flown to the alternate integration site. The
Pegasus will be demated from the OCA,
transported to the integration facility, the fairing will
be removed, payload integration activities will be
conducted, the fairing will be reinstalled, and the
Pegasus will be transported back to the OCA and
prepared for launch.
10.2. Alternative Launch Sites
Authorize by: L-24 months
To support trajectories not attainable without
significant trajectory dog-leg from Vandenberg, the
Pegasus can be launched from the following
ranges:
 Eastern Range;
 Wallops Flight Facility;
 Reagan Test Site (RTS), Kwajalein, Republic
of the Marshall Islands; and
 Other ranges are possible and will be
investigated on a case-by-case basis and may
require inter-governmental coordination.
This assumes that the rocket and payload
integration takes place at Vandenberg and the
integrated launch vehicle/satellite is ferried to the
launch site on the OCA and launched without
demating from the OCA. Integration facilities will
not be provided at the range location.
10.3. Downrange Telemetry Support
Authorize by: L-12 months
Orbital has established relationships with a
number of Government organizations to provide
telemetry coverage beyond the capability of the
launch-range fixed telemetry assets. These
mobile assets can be deployed in advance to an
appropriate downrange location or in near real-
time (airborne systems) to support the acquisition
of telemetry from either Pegasus or spacecraft
(spacecraft telemetry downlink dependent)
telemetry. These systems have been used
successfully on a number of Pegasus missions
and prove to be an effective means of collecting
telemetry for real-time re-transmission or for post-
flight data review. Orbital will coordinate
spacecraft requirements with the mobile range
provider to ensure that appropriate operational
support and data products are provided to the
payload customer.
10.4. Additional Fairing Access Doors
Authorize by: L-24 months
Additional access doors are available. Standard
sizes are 8.5” x 13” and 4.5” circular. The
following restrictions apply to door location.
The additional access doors are 13” x 8.5”. The
long dimension must be aligned with the Pegasus
x-axis. The number of access doors in each half
of the fairing cannot exceed two. Each additional
door has an impact on payload performance to
orbit of approximately 1 kg (2.2 lbm) each.
The additional rectangular access doors can be
located in the standard zone in the cylinder section
or at pre-approved locations in the ogive section of
the fairing. Doors located in the pre-approved
zone of the cylinder section are subject to the
same restrictions that apply to the standard
service doors.
The additional rectangular access doors can be
located in the ogive section of the fairing. The
center of the door must be located at fairing
station 137.94 (equates to station 652.74 of
Pegasus) with an angular location between 35

and 145  on the starboard half of the fairing or
between 215  and 325 on the port half. Only one
door is allowed in the ogive section of each half of
the fairing. The placement of an access door in
the ogive may reduce the local payload static and
dynamic envelope by an amount equivalent to the
door doubler thickness. A clearance analysis will
be performed as part of the nonstandard service.