Injection system for hybrid rocket propulsion unit

摘要

In an injection system for a hybrid rocket propulsion unit, the liq. component is passed through small channels (2) in the fuel block (3) to the combustion face of an inner burner so that an optimal fuel/oxidiser mix ratio is obtd. at each point of the combustion surface. The channels extend radially from the combustion chamber periphery to its interior, repeatedly intersect the combusted gas flow direction at an angle or orthogonally and are in the form of either simple bores through the solid fuel or tubes e.g. of metal, the channel system disappearing during the combustion process. The channel arrangement provides the desired burn-off properties and geometry by local grouping, concn. bore changes or blind ends which are subsequently opened during fuel combustion. The channels are supplied with oxidiser in groups which can be regulated individually or in their entirety.