| 摘要 |
Propulsion device, especially for kinetic projectiles, comprising a reserve of liquid propellant burning in a combustion chamber followed by a propelling nozzle, characterised by the fact that the reserve of liquid propellant is stored in the form of a column of liquid 42 directly in the combustion chamber 32, that the column of liquid is supported by a limiting wall 30 at the end of the combustion chamber located to the rear in the direction of flight A and that a return duct 50, 52, 54 leading from the front end of the combustion chamber towards the propelling nozzle 40 is provided for the hot propellent gases escaping during combustion of the column of liquid. <IMAGE>
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