| 摘要 |
The invention relates to a combustion gas discharge nozzle for a rocket engine comprising a stationary part (1) and a moving part (2), extending the stationary part, said moving part, made using flaps (2a, 2b), being positioned downstream from the stationary part and forming an extension of the nozzle, the nozzle comprising a sealing device between the fixed part and the moving part in the form of a flexible membrane (4) 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 (4) forming an annular tubing, the device being provided with means (5) for injecting gas at the flexible membrane between the stationary part (1) and the moving part (2) extending said nozzle. |
