Orbital Minotaur IV - Manual (Page 2)

Minotaur IV
Payload Accommodations
• Standard 2.34 m (92 in) diameter spacecraft fairing
• Mission-specific fairing access doors for spacecraft support
• Spacecraft and fairing assembly integrated independently from launch vehicle
stages
• Well-defined launch environments derived from extensive flight data
• Temperature, humidity, and cleanliness control through lift-off
• Standard 986 mm (38.81 in) diameter bolted interface with optional spacecraft
support options
- Single and multiple spacecraft adaptors
- Various flight-proven spacecraft separation systems available, including low-
shock designs
• Multiple Payload Adapter Fitting (MPAF) option
• Hydrazine upper stage for multiple orbit altitude capabilities or increased orbital
insertion accuracy
Performance
• System performance assured from extensive booster motor flight history of
more than 50 flights each
• Typical orbit accuracy better than ±5 km insertion apse, ±25 km non-insertion
apse, and ±0.1 deg inclination (3-sigma values)
• Optional enhanced insertion accuracy available
• Cold gas attitude control system readily accommodates a variety of spacecraft
mission requirements, including precise separation pointing and post-boost
maneuvers
• Minotaur IV with optional STAR ™ 48BV Stage 4 provides up to 225 kg increased
performance to LEO and support for HEO missions
Ø0.48 m
(19.2 in)
0.87 m
(34.5 in)
1.52 m
(60.0 in)
2.87 m
(113.3 in)
Ø2.05 m
(Ø80.9 in)
Ø38.81 in Interface
(No Sep System)
Fairing Sep Plane
Ø1.33 m
(Ø52.5 in)
Standard Fairing
Copies of the Minotaur User's Guide
can be downloaded from:
www.orbital.com
Additional information should be obtained
from the USAF OSP Office
USAF SMC Space Development
and Test Directorate (SMC/SD)
Launch Systems Division (SMC/SDL)
Kirtland AFB, NM 87117-5778
(505) 853-5533 (505) 853-0507
For technical details or questions
please contact Orbital at:
[email protected]
200 400 600 800 1000 1200 1400 1600 1800
1600
1400
1200
1000
800
600
400
Orbit Altitude (km)
Pa
yl
oa
d (
kg
)
CCAS 28.5 °
WFF 43 °
VAFB 72 °
Kodiak 63.4 °
VAFB Sun-Synch
NOTE: Payload Mass includes
Adapter Cone, Separation
System and Other Mission-
Specific Hardware *
*
* Detailed Analysis Needed for
Missions to These Altitudes
Orbital Sciences Corporation
45101 Warp Drive • Dulles, Virginia 20166 • www.orbital.com
©2014 Orbital Sciences Corporation BR06005_2429