| 摘要 |
<p>A dual thrust rocket propulsion machinery is disclosed. The present invention comprises: a first combustion chamber in which a first propellant and a first ignition system for ignition of the first propellant are disposed therein, and which maintains a heat structural form from combustion gas generated from the ignition of the first propellant; a hollow pipe which protrudes from the first combustion chamber to generates the thrust by discharging the combustion gas; and a second combustion chamber in which a second propellant is positioned to surround the hollow pipe in a longitudinal direction.</p> |
