HYBRID ROCKET ENGINE Russian patent published in 2009 - IPC F02K9/72 

FIELD: engines and pumps.

SUBSTANCE: invention relates to space engineering and can be used for development of hybrid rocket engines. The proposed hybrid rocket engine incorporates a charge chamber housing a solid fuel component charge with a through channel made along its axis, nozzle head, fuel supply line with the fluid fuel component tank, control and parametre control elements. The fuel solid component charge represents a cylinder or ellipsoid of rotation. The fuel solid component charge has one or several radial annular slots or a number of channels starting from the axial channel boundaries. The nozzle head features the shape approximating, most possibly, to that of ignited solid fuel component surface. The nozzle head accommodates the jet and centrifugal nozzles, arranged as alternating belts, that communicate with separate manifold chambers. The fuel liquid component feed line connected with the component feed control system adjusted for linear variation of pressure in the manifold chambers.

EFFECT: improved specific properties, reduced sizes and weight, labour input and costs.

2 cl, 5 dwg