Orbital Minotaur VI - Manual

Fact Sheet
Quick FactS
System Features
• Full spacecraft integration support,
including mission management,
spacecraft interface support (power,
telemetry, sequencing, attitude
control, and deployment), through
launch operations and post-launch
performance evaluation
• Flexible design enables multiple
mission tailoring options
• Cost effective space launch
• Responsive launch solutions available
• Mission success is ensured by mature
systems and processes
- Orbital’s rigorous mission assurance
program
- Full government insight and
independent assessment
• Multiple spaceport launch capability
(Florida and Alaska) using portable
ground support equipment
Overview
Minotaur VI is an evolutionary version of the flight proven Minotaur IV+ Space Launch Vehicle (SLV),
providing a cost-effective and capable space solution for U.S. Government-sponsored spacecraft.
The combination of four government-furnished solid rocket stages, a commercial solid rocket upper
stage, and Orbital’s flight-proven systems and processes provide unmatched value and performance.
The integration of government motors with commercial boosters and state-of-the-art hardware is one
of Orbital’s unique strengths that spans several decades of experience.
The Minotaur VI vehicle adds a lower stage to the existing and flight demonstrated Minotaur IV+
vehicle for a significant increase in performance with only a modest increase in cost. The only new
structure required is the 1/2 interstage, which is adapted from a heritage flight proven design to
minimize risk. For elliptical or high energy missions, a STAR
™ 37 upper stage option is available.
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 VI provides cost effective support of
medium-small LEO and high energy missions.
Minotaur VI
Space Launch Vehicle
Expanded view of the Minotaur VI launch vehicle
SR118
SR118
SR119
SR120
Payload
Adapter
Module (P
AM)
Guidance Control
Assembly (GCA)
Frangible Ring
• Separates S4
4/5 Interstage with
Extension Structure
Payload Fairing
• 2.3 m (92 in.) Diameter
Fairing Adapter Ring
• Frangible Separation
Ring
Payload Adapter Cone
• Fixed 986 mm (38.81 in.)
Interface
• Optional 1.19 m or 1.57 m
Interface
Stage 5 Motor
• STAR 48BV
GCA Skirt
• Antennas/
Umbilical
Interface
Motor Adapter Cone
Avionics Structure
• Integrated Avionics Assembly
- Flight Computer
- INS
- MACH Avionics
- Batteries
- Attitude Control System
- Booster Control System
- Telemetry System
- FTS System
- GPS Tracking System
Stage 1
Assembly
Stage 2 Assembly
Stage 3 Assembly
Stage 4 Assembly
1/2 Interstage
• Vented Interstage
Existing/Flight Proven
Adapted from Existing
Flight-Proven Design