Credit: © Mark Wade
H2O2/Kerosene propellant rocket stage. Loaded/empty mass 83,560/6,883 kg. Thrust 443.19 kN. Vacuum specific impulse 335 seconds. Winged, single stage to orbit launch vehicle using aerial refueling and lower performance, non-cryogenic propellants. Takes off from runway at 48,452 lbs gross weight; rendezvous with tanker to load 146,870 lbs oxidizer; then flies to orbit.
No Engines: 7. Release conditions: 800 kph at 8.5 km.
Status: Study 1993.
More... - Chronology...
Gross mass: 83,560 kg (184,210 lb).
Unfuelled mass: 6,883 kg (15,174 lb).
Height: 57.50 m (188.60 ft).
Diameter: 6.30 m (20.60 ft).
Span: 39.50 m (129.50 ft).
Thrust: 443.19 kN (99,633 lbf).
Specific impulse: 335 s.
Burn time: 560 s.
JP-5/H2O2 Notional H2O2/Kerosene rocket engine. 63 kN. Study 1993. Isp=335s. Engine for Black Horse winged, single stage to orbit launch vehicle using aerial refueling. More...
Associated Launch Vehicles
Black Horse American air-launched winged orbital launch vehicle. Winged, single stage to orbit launch vehicle using aerial refueling and lower performance, non-cryogenic propellants. Takes off from runway at 22,000 kg gross weight; rendezvous with tanker to load 66,760 kg oxidizer; then flies to orbit. More...
H2O2/Kerosene Hydrogen peroxide is used as both an oxidiser and a monopropellant. Relatively high density and non-toxic, it was abandoned after early use in British rockets, but recently revived as a propellant for the Black Horse spaceplane. Rocket propellant RP-1, or its foreign equivalents, is a straight-run kerosene fraction, which is subjected to further treatment, i.e., acid washing, sulphur dioxide extraction. Thus, unsaturated substances which polymerise in storage are removed, as are sulphur-containing hydrocarbons. More...
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