Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
Liquid Air/Lox/LH2
Liquid Air/Lox/LH2 propellant. Liquid air has no advantage as a stored propellant, but in a Liquid Air Cycle Engine (LACE) relatively freely available atmospheric air is scooped up, liquefied, and burned with a fuel in a conventional rocket engine. In this variant, liquid oxygen is used to continue operation of the engine above the atmosphere, allowing the engine to be used in single-stage-to-orbit designs. This approach was used by Rolls Royce in the RB545 engine proposed for the HOTOL spaceplane, but later abandoned for the simpler Air/Lox/LH2 Sabre engine for the proposed Skylon SSTO.

Fuel Density: 0.071 g/cc. Fuel Freezing Point: -259 deg C. Fuel Boiling Point: -253 deg C.



Subtopics

RB545 Rolls Royce air augmented rocket engine. Used Liquid Air/LOx/LH2. Development ended 1985. Used on HOTOL launch vehicle.

Engines: RB545.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use