| 摘要 |
The engine has a fixed fuel block (2) arranged with radial symmetry, with sector-shaped hollow spaces (3) along the length of the fuel block to form the combustion chamber of the engine. The hollow spaces end blindly in fuel in the flight direction and open in the direction of a convergent-divergent nozzle (4) to allow free passing of combustion gases. A single, central oxidator supply pipe (1) is arranged inside the length of the fuel block. The oxidator supply pipe is open in the flight direction and is closed and pressure sealed in the nozzle direction. The oxidator supply has a number of smaller channels (5) corresponding to the number of hollow spaces, so that each channel opens into the point of a hollow space. The channels are distributed over the length of the rocket. The oxidator supply pipe has an opening (7) at each branch point for a channel, which is narrower than the channel and through which oxidator is injector into the system of hollow spaces, so that the oxidator is not directly applied to the fuel wall of the channel.
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