Secondary jetting structure of hydrogen peroxide solid-liquid mixing rocket engine afterburner room

Abstract

The invention discloses a secondary jetting structure of a hydrogen peroxide solid-liquid mixing rocket engine afterburner room and belongs to the field of solid-liquid mixing rocket engines. The secondary jetting structure of the afterburner room comprises inlet filler necks, accumulated liquid cavity outer rings, accumulated liquid cavity inner rings, capillaries, jetting panels and heat insulation plates, and the inlet filler necks, the accumulated liquid cavity outer rings, the accumulated liquid cavity inner rings, the capillaries, the jetting face plates, and the heat insulation plates are symmetrical; the secondary jetting structure and the afterburner room are designed integrally; hydrogen peroxide enters accumulated liquid cavities from the two inlet filler necks correspondingly, the accumulated liquid cavities are composed of the accumulated liquid cavity outer rings and the accumulated liquid cavity inner rings in a surrounded mode, the hydrogen peroxide flows into the jetting panels from the accumulated liquid cavities through the capillaries and penetrates through holes in the heat insulation plates, and the hydrogen peroxide is jetted into the afterburner room and participates in burning. According to the secondary jetting structure of the hydrogen peroxide solid-liquid mixing rocket engine afterburner room, heat transmission from the afterburner room to the jetting panels is reduced by adopting the heat insulation plates, heat transmission from the jetting panels to the accumulated liquid cavities is reduced by adopting capillary structures, risk of explosion caused by high temperature of the hydrogen peroxide in the accumulated liquid cavities is avoided, reliability and safety of the solid-liquid mixing rocket engine are improved, and burning efficiency of the solid-liquid mixing rocket engine is improved.

Description

technical field [0001] The invention belongs to the field of solid-liquid hybrid rocket engines, and in particular relates to a hydrogen peroxide solid-liquid hybrid rocket engine afterburning chamber secondary injection structure. Background technique [0002] The solid-liquid hybrid rocket engine has the advantages of good safety, adjustable thrust, multiple starts, reliable operation and low cost. The secondary injection technology is the secondary injection of the oxidant in the afterburner of the solid-liquid mixed rocket engine. [0003] The solid-liquid hybrid rocket engine effectively improves the combustion efficiency through the secondary injection, and improves the fuel-rich combustion in the upper half of the fluid channel of the solid-liquid hybrid rocket engine, which is rich in oxygen and in the second half, so that the propellant of the solid-liquid hybrid rocket engine The combustion is more complete, thereby improving the working performance of the solid-l...

AI Technical Summary

Problems solved by technology

[0004] However, for the hydrogen peroxide propellant, there is an obvious technical problem in the secondary injection structure of the afterburner of the solid-liquid hybrid rocket engine, that is, the temperature of the afterburner is relatively high.

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