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Lockheed Launch Vehicle (LLV)

Background Information
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

Other Resources


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