Orbital Pegasus - Manual (Page 69)

Release 7.0 Apr 2010 58
Pegasus User’s Guide
transmitted around the lower spacecraft via the
DPAF structure, thus avoiding any structural
interface between the two payloads.
For the upper payload the DPAF uses either an
Orbital standard 97 cm (38 in.) Marmon clamp
band interface, or an Orbital 59 cm (23 in.)
Marmon clamp band interface on a separable
adapter cone. The aft satellite support structure
consists of either an Orbital 59 cm (23 in.)
separation system, or an Orbital 43 cm (17 in.)
separation system, both of which include an
adapter cone to transition to the 97 cm (38 in.)
diameter Pegasus third stage.
The separation systems are aluminum Marmon
clamp designs. Each satellite is provided an
independent electrical interface to the launch
vehicle.
The separation sequence for the stack begins with
initiation of the forward payload separation system
followed by the separation of the conical adapter
(if present). The aft payload is then separated and ejected from within the cylinder that remains with
the third stage.
10. NONSTANDARD SERVICES
Orbital offers a wide variety of nonstandard
services. This section describes optional
nonstandard services that are available. Within
the description of each nonstandard service, the
required authorization time is provided. Many of
these nonstandard services have flight heritage on
one or more Pegasus flights.
10.1. Alternative Integration Sites
Authorize by: L-24 months
Pegasus can offer the following sites for payload
integration:
 Eastern Range;
 Wallops Flight Facility; and

Other sites are possible and will be
investigated on a case-by-case basis and may
require inter-governmental coordination.
Figure 9-2. Dual Payload Attach Fitting Configuration