FACT SHEET

Minotaur I Space Launch Vehicle

The Minotaur I Space Launch Vehicle

The Minotaur I Space Launch Vehicle (SLV) provides a responsive, reliable, and cost-effective launch solution for U.S. Government sponsored spacecraft. In addition to a demonstrated successful history over its initial and subsequent launches, it builds on a long background of dependable launch systems. The Minotaur I uses residual Minuteman II first and second stages in combination with the upper two stages shared with Orbital’s Pegasus XL and Taurus XL commercial SLVs. The Minotaur family of launch vehicles is provided via the Orbital/Suborbital Program 2 (OSP-2) of the U.S. Air Force Space and Missile

Systems Center (SMC) Rocket System Launch Program (RSLP).

Features:

• Inertially guided four stage solid rocket propulsion

• Flight-proven systems with demonstrated success record

• Multiple spaceport launch capability (California, Florida, Alaska, Virginia) using portable ground support equipment

• Full payload integration support including mission management, spacecraft interface support (power, telemetry, sequencing, attitude control, and deployment), and launch operations

• Standard 18 month mission response including payload integration and launch by Orbital’s experienced launch crews

• Responsive launch solutions from 6 months to 48 hours available

Minotaur I Space Launch Vehicle

Success on First Five Missions

Innovation You Can Count OnTM

0.0

MM 1/2INTERSTAGE

2/3 INTERSTAGE

AVIONICSASSEMBLY

ORION 38

3/4 INTERSTAGE

PAYLOADFAIRING

PAYLOAD I/F

FAIRING SEP

S2/S3 SEP

52.0 IN. DIA

65.76 IN. DIA

(Dimensions in Inches)

50.0 IN. DIA

S1/S2 SEP

754.7

650.15

580.85

494.75

441.05

340.52

289.50274.43

51.79

SR19

ORION 50XL

M55

JAWSAT – Jan 2000 MightySAT II.1 – Jul XSS-11 – Apr 2005 STP-R1 – Sep 2005 COSMIC – Apr 2006

Orbital Sciences CorporationLaunch Systems Group3380 South Price RoadChandler, Arizona 85248

www.orbital.com© 2006 Orbital Sciences Corporation

BR06003

Minotaur I Specifications

Performance:

• Flight-verified system performance

• Proven secondary payload capability

• Adaptable to a variety of payloads and orbital requirements with typical accuracy of 33.4 nm (3s), 0±0.1 deg inclination (3s)

• Optional Soft Ride for Small Satellites (SRSS) to mitigate flight dynamics environments

• Available optional enhancements include:

- Insertion accuracy of <10 nm (3s) inclinations <0.05 deg (3s)

- Conditioned air (Class 10K), temperature and humidity control and nitrogen purge

- Additional payload access panels

Standard 50” Fairing Optional 61” Fairing

Minotaur I Payload Capability

Program Office:Additional information should be obtained from the USAF OSP Office USAF SMC Space Development & Test Wing Rocket System Launch Program (RSLP) 3548 Aberdeen Avenue S.E. Kirtland AFB, NM 87117-5778 (505) 846-8957 FAX: (505) 846-1349

31.0

AVAILABLEENVELOPE(DYNAMIC)

INTERFACE PLANE

87.8

47.3

0

50.0

47.0

151.5

131.3

80.1

0.0

54.7

35.4

INTERFACE PLANE

22.7

AVAILABLEENVELOPE(DYNAMIC)

0 100 200 300 400 500 600

Payload (kg)

Apo

gee

(km

)

0

200

400

600

800

1000

1200

1400

1600

1800

2000

CCAS 28.5°

VAFB 72°

WFF 38°

VAFBSun-Synch Kodiak

64°

NOTE:1. Payload Mass includes

Adapter Cone, Separation System and Other Mission-Specific Hardware.

Payload Accommodations:• Standard 50 in. Pegasus-design payload fairing

• Optional 61 in. fairing for larger or multiple payload missions

• Thermally controlled fairing volume with Class 100K standard cleanliness

• Well defined launch environments

• Variety of proven payload separation systems available

Point of Contact:For Technical Details, Please Contact Us At: Phone: 480.814.6566 E-mail: minotaur@orbital.com Website: www.orbital.com

Innovation You Can Count OnTM

Simplified Horizontal Payload Integration