Orbital Minotaur V User Manual
FACT SHEET
Minotaur V
High Energy Space Launch Vehicle
Overview
Minotaur V is a ve stage
evolutionary version of the
Minotaur IV Space Launch
Vehicle (SLV) to provide a costeffective capability to launch
U.S. Government-sponsored
small spacecraft into high
energy trajectories, including
Geosynchronous Transfer Orbits
(GTO) as well as translunar and
beyond.
The Minotaur V concept
leverages Orbital’s ight proven
heritage of the Minotaur family
of launch vehicles to create
a low-risk, readily-developed
system.
The Minotaur V avionics,
structures, and fairing are
common with the Minotaur IV
SLV, with relatively minor
changes to create the ve stage
conguration. Moreover, the
avionics and ight software
are highly common across all
Minotaur family vehicles.
The rst three stages of the
Minotaur V are former
Peacekeeper solid rocket
motors with over 50 ights of
each stage. The fourth and fth
stages are commercial STAR
fth stage can be either attitude controlled or spinning. For a spin-stabilized upper stage, a STAR™
37FM is used while a STAR™ 37FMV, with gimballed, exseal nozzle, is used for 3-axis stabilized
control.
The Minotaur family of launch vehicles are provided via the Orbital/Suborbital Program (OSP)
managed by the U.S. Air Force Space and Missile Systems Center (SMC), Space Development and
Test Directorate (SMC/SD) Launch Systems Division (SMC/SDL) located at Kirtland Air Force Base,
New Mexico.
Minotaur V provides cost-effective support of small GEO and lunar missions.
™
motors. The stage four motor is a STAR™ 48BV conguration. The
QUICK FACTS
System Features
• Near term cost effective support of
high energy trajectory missions
• Straight forward ve stage evolution of
Minotaur IV SLV
• Extensive use of ight-proven
boosters, subsystems, and software
• Inertially-guided or spinning Stage 5
conguration options available
• Portable ground support systems
allow multiple spaceport launch
capability (California, Florida, Alaska,
Mid-Atlantic)
• Mission success ensured by mature
systems and processes including
Orbital’s rigorous mission assurance
program, full government insight, and
independent assessment
Minotaur V is a low risk direct evolution of
Minotaur IV.
Minotaur V
Performance
• Minotaur V has a GTO capabilit y of 532 kg
- 185 km x 35786 km @ 28.5 degree
1800
160 0
140 0
inclination, 180 AoP
• Minotaur V has a MTO capability at 39 degrees of
650 kg from CCAFS
- 185 km x 20,200 km at 39 Degree inclination,
180 AoP
• Minotaur V has a MTO capability at 55 degrees of
1200
1000
Payload (kg)
800
600
603 kg from WFF
- 185 km x 20,200 km at 55 Degrees
400
inclination, no AoP constraint
• Minotaur V has a TLI capability of 342 kg
-60 -40 -20 0 20 40 60
Payload Accommodations
• Flight proven fairing shared with Minotaur IV
• Attitude controlled or spinning nal stage
• Well dened environments from extensive ight data and well characterized
upper stages
• ISO 8 (100 k) to ISO 7 (10 k) cleanliness with temperature and humidity control
• Various ight-proven separation systems available, including low shock designs
C3 (km2/s2)
0.87 m
(34.5 in)
1.52 m
(60.0 in)
Minotaur V
Inclination: 37.8˚
Direct Ascent
Perigee: 185 km
No Argu ment of Pe rigee Restriction
Ø0.48 m
(19.2 in)
Ø1.33 m
(Ø52.5 in)
For technical details or questions
please contact Orbital at:
minotaur@orbital.com
Orbital Sciences Corporation
45101 Warp Drive
•
Dulles, Virginia 20166
Copies of the Minotaur User's Guide
can be downloaded from:
www.orbital.com
•
www.orbital.com
Ø2.05 m
(Ø80.9 in)
STAR 37
Ø38.81 in
Interface
(No Sep System)
Secondary
Paylo ad Volume
(Negotiable)
Fairin g Sep Plan e
1.72 m
(67.7 in)
Additional information should be
from the USAF OSP Ofce
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
obtained
©2014 Orbita l Sciences Corporatio n BR060 06_2429
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