| 摘要 |
A thrust nozzle for solid-fuel rocket motors, which thrust nozzle is installed inside the motor structure and is constructed as a hollow annular housing which extends in the longitudinal direction of the motor and is designed in a similar manner to an offset parallelogram in cross-section whose shorter, front, radially outer annular wall and whose shorter, front, radially inner annular wall together project in the form of a wedge into the combustion chamber, the front, radially inner annular wall being used for the arrangement of a solid ring which forms the contour of the nozzle neck and is thermally resistant, while the rear, radially outer annular wall is, in particular, cylindrical and is detachably or non-detachably connected to the motor housing (1) and, furthermore, the rear, radially inner annular wall forms the rear part of the divergent thrust-nozzle region. <IMAGE>
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