Reaction propulsion using internally stored oxygen for combustion of the fuel. Propellants may be single compounds, eg hydrogen peroxide, or separately stored fuel, eg liquid hydrogen, and oxidizer, eg liquid oxygen. Used primarily where there is insufficient atmospheric oxygen, eg above 70 000 ft 20 km, or where the lightness and compactness of the motor offset the high propellant weight, eg for assisted take-off and missiles. See panel on Rocket.

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