Orbital Pegasus - Manual (Page 49)

Release 7.0 Apr 2010 38
Pegasus User’s Guide
5.4.7. System Safety Constraints
Orbital considers the safety of personnel and
equipment to be of paramount importance. The
payload organization is required to conduct at
least one dedicated payload safety review in
addition to submitting to Orbital an Accident Risk
Assessment Report (ARAR) or equivalent as
defined in AFSPCMAN 91-710.
Organizations designing payloads that employ
hazardous subsystems are advised to contact
Orbital early in the design process to verify
compliance with system safety standards.
AFSPCMAN 91-710 outlines the safety design
criteria for spacecraft on Pegasus vehicles. These
are compliance documents and must be strictly
adhered to. It is the responsibility of the payload
contractor to ensure that the payload meets all
Orbital and range imposed safety standards.
5.5. Carrier Aircraft Interfaces
5.5.1. Payload ASE Provisions
As a standard service, Orbital will provide up to 8U
of space within an EIA 19” rack mount chassis at
the LPO Station on the Carrier Aircraft for pay-
load ASE. Power provided for payload ASE is
110 VAC, 60 Hz at maximum current of 15 A.
Orbital will generate required drawings, submit
required documentation to the FAA for approval
and perform the installation of the payload
equipment in the aircraft. If required due to the
volume of payload ASE, a separate payload-
provided equipment rack can be installed on the
carrier aircraft as a nonstandard service.
As a standard service, Orbital will provide
redundant DC power supplies and a switch panel
in the LPO Station on the OCA that are dedicated
for use by the payload. These power supplies
may be used to provide spacecraft power and
battery charging during ground operations and
captive carry up until L-12 minutes at which time
the spacecraft must transition to internal power.
The power supplies can provide 60 V at 15 A
maximum.
Figure 5-14 provides details on the Pegasus/OCA
interface. The electrical interface between
payload ASE and the carrier aircraft will be
documented in a mission-specific EICD.
Figure 5-14. Pegasus/OCA Interface Details