Encyclopedia Astronautica
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.

Selected propellants for Black Horse 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.

Propellant Formulation: H2O2/JP-5.

Status: Study 1993.
Thrust: 63.00 kN (14,162 lbf).
Specific impulse: 335 s.
Burn time: 560 s.

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Associated Countries
See also
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...

Associated Propellants
  • 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...

Associated Stages
  • Black Horse 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. More...

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