| 摘要 |
The invention relates to a combustion gas discharge nozzle for a rocket engine including a stationary part and a moving part, extending the stationary part, the moving part, made using flaps, being positioned downstream from the stationary part and forming an extension of the nozzle, the nozzle including a sealing device between the fixed part and the moving part in the form of a flexible membrane withstanding a local temperature of the combustion gases at the nozzle outlet and connecting the end of the stationary part to a border of the flaps or petals forming the moving part, the flexible membrane forming an annular tubing, the device being provided with means for injecting gas at the flexible membrane between the stationary part and the moving part extending the nozzle. |
