| 摘要 |
The invention describes a hybrid rocket injection system designed to increase combustion efficiency and fuel regression of large and powerful motors of the internal burning type, whereby said injection system consists of a multitude of fine tubes originating at the periphery of the motor case and running radially through the solid fuel block towards a centrally located port, the effect being a thorough mixing of oxidizer and gasified fuel independent of port length. Oxidizer flow per fuel surface area can be kept constant throughout operation. By creating multiple sites with direct contact of oxidizer and fuel, fuel regression is no longer dependent on the fuel's previous gasification. The more feed tubes are provided, the better the invention will work. Their number, arrangement and layout allows to constructively predetermine the burn characteristic of the fuel block. Said feed tubes or subsets are advantageously supplied through ducts running along the inside or outside of the motor case, whereby oxidizer flow to given subsets of feed tubes as multiple dependents of a common supply pipe can be controlled by regulating the flow into these pipes.
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