| 摘要 |
<p>The invention relates to a multi-pulse operable rocket engine and reconfigurable structure depending on the mission requirements which may be used for equipping and propelling rockets requiring long operation durations for the propulsion system within ranges imposed by the flight speed variation on elongated paths. According to the invention, the rocket engine is characterized by the fact that it has a propulsion charge in the shape of several fuel rods (10 and 19) whose ignition and combustion is successively carried out, at given time intervals, and the reconfigurable structure is obtained by assembling the engine from several sections (B, C) fuel chambers joined to one another by means of connection elements (D, E), the number of sections and the delay period in successively functioning thereof being established depending on the desired path.</p> |
