| 摘要 |
This invention concerns the piloting of propulsion systems for solid rocket propellant missiles. It consists of a piloting assembly in which the front section of a thrust nozzle integrated in the body of a propulsion system is pierced with at least three orifices which can be covered by means of valves and which are designed to provide direct injection into the thrust nozzle of hot gases from the powder block of the propulsion system to pilot the missile. An auxiliary block of "cold" powder is fitted around the nozzle on the input side of the orifices. The application is for piloting of ballistic missiles.
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