| 摘要 |
<p>The invention relates to a device for reducing the thrust of jet engines, especially rocket engines, with at least one propellant charge arranged in a fuel chamber, an igniter and a nozzle (2) for the directed outflow of the propellent gases. So that short ranges are possible without at the same time having to adjust the launch angle to values less than the usual minimum launch angle, it is proposed according to the invention that, for alternative adjustment of the thrust level, at least two swivelling pipe bends (12) be arranged around the nozzle (2) so that in the retracted position one leg (20) of the pipe bend (12) is immersed in the gas jet and diverts a portion of the propellent gases. <IMAGE></p> |
