| 摘要 |
The invention relates to a solid propellant rocket engine which is designed in such a way that it can temporarily increase its thrust at a required stage of its operation. The engine has a first propellant structure which is fixed in the combustion chamber and is designed with a hole, which intersects an initial combustion surface of the structure, and a second propellant structure which is fitted displaceably and gas-tightly into the hole of the first structure and is shorter in length than the said hole. Initially the second structure is prevented from moving relative to the first structure by a retaining mechanism which, for example, comprises a piston, which extends into an end section of the said hole and comes into contact with one end surface of the second structure. At a desired point during the operation of the engine the retaining mechanism can be disabled by actuation of a release device, the second structure being forced to move by the combustion gas pressure with the result that one end section of the inner surface of the first structure, which forms the hole, is exposed and becomes an additional combustion surface. The two structures are generally formed and arranged in such a way that they form one structure essentially burning endwise. <IMAGE>
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