Encyclopedia Astronautica
Falcon SLV-1


Michoud Lox/Solid hybrid rocket engine. 1400 kN. First stage. Study 2005. Part of the USAF FALCON program to assess hybrid propulsion applications for a responsive small launch vehicle.

In November 2003, Lockheed Martin-Michoud Operations was awarded a six-month study contract from DARPA as part of the USAF FALCON program to assess hybrid propulsion applications for a responsive small launch vehicle. This study concluded in May 2004. In September 2004, FALCON competitors began a 10-month design phase to be followed by a down-select to possibly two competitors, and a winning design to be selected in 2007. Lockheed Martin-Michoud's all-hybrid two-stage vehicle would deliver a payload up to 455 kilograms to LEO and, if selected, would establish hybrid propulsion as a viable space launch booster technology. The core booster stage would generate approximately 1.4 million newtons of thrust.

Application: First stage.

Characteristics

Propellant Formulation: Lox/HTPB.

Status: Study 2005.
Thrust: 1,400.00 kN (314,700 lbf).

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Associated Countries
See also
Associated Manufacturers and Agencies
  • Michoud American manufacturer of rocket engines and rockets. Michoud, USA. More...

Associated Propellants
  • Lox/Solid Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

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