Evaporative wick/membrane rocket motor

摘要

A bi-propellant rocket motor 15 for combusting fuel 16 and oxidiser 17 to produce thrust. The rocket motor has a tubular casing 18, a combustion chamber 3 disposed radially inwards of the casing 18, and a means for supplying fuel 404 to the combustion chamber. Also provided is a means for supplying oxidiser 402 to the combustion chamber. The combustion chamber includes a porous membrane 4 and in use, fuel is supplied to the combustion chamber via the membrane and combusts in oxidiser supplied to the combustion chamber. The wall of the combustion chamber may comprise the porous membrane. The tubular casing and the porous membrane may form a void 5 for receiving fuel supplied to the combustion chamber. A nozzle 1 may be connected to the combustion chamber. The means for supplying fuel to the combustion chamber may be configured such that a portion of the fuel supplied to the combustion chamber may remain unburnt and passes along an inner surface of the membrane and nozzle to reduce ablative erosion of the nozzle.