Lockheed Launch Vehicle (LLV)

First Launch:

August 1995 (Demonstration Launch Vehicle)

Flight Rate:

6-10 per year (capability)

Launch Site:

SLC-6 (VAFB, USA), LC-46 (CCAS, USA)

Capability:

1,750 lb to LEO

History

• Early 1990s Lockheed Missiles and Space Corporation began studies on the prospect of a new family of small launch vehicles for commercial and other users
• Lockheed approved the Lockheed Launch Vehicle (LLV) program in January 1993
• Completed the Pathfinder exercise to verify assembly and procedures in July 1994
• First LLV-1 demonstration flight August 1995

Description

• Two-stage vehicle
• Stage 1 uses one Thiokol Castor 120 motor that burns HTPB propellant, generating 370,990 lb of thrust
• Stage 2 uses one United Technologies Orbus 21D that burns HTPB propellant, generating 43,250 lb of thrust
• Olin Aerospace’s Attitude Control System, located within the OAM, contains a total of 10 MR-107 rocket engines, each generating 50 lb of thrust, performing orbit injection correction and attitude control functions
• Litton’s LN-100L inertial guidance system provides guidance outputs to the LLV avionics processor for orbit placement

Profile

Length:

65 ft

Launch Weight:

145,000 lb

Diameter:

7.7 ft

Liftoff Thrust:

370,990 lb

Payload Fairing:

14.1 ft x 6.5 ft