Oxygen-fuel ratio offset control method for solid-liquid rocket engine

The invention discloses a solid-liquid rocket engine oxygen-fuel ratio offset control method which comprises the following steps: designing the number of spiral blades of a spiral nested grain, and regulating and controlling the injection mode of an oxidizing agent introduced into a combustion chann...

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Bibliographic Details
Main Authors WANG ZEZHONG, YU XILONG, LI FEI, LIN XIN, MENG DONGDONG, ZHANG ZELIN, LUO JIAXIAO
Format Patent
LanguageChinese
English
Published 12.08.2022
Subjects
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:The invention discloses a solid-liquid rocket engine oxygen-fuel ratio offset control method which comprises the following steps: designing the number of spiral blades of a spiral nested grain, and regulating and controlling the injection mode of an oxidizing agent introduced into a combustion channel in the spiral nested grain to adjust the retreating rate of a combustion surface; the spiral nested grain with the same number of spiral blades is selected to be combined with different injection modes for oxygen-fuel ratio testing, so that the influence rule of the injection modes on the retreating rate of the combustion surface is obtained, and then the optimal injection mode is obtained; different numbers of helical blades and helical blades in the optimal injection mode are selected for oxygen-fuel ratio testing, so that the influence rule of the number of the helical blades on the retreating rate of the combustion surface is obtained, the number of the optimal helical blades is further obtained, and the com
Bibliography:Application Number: CN202210666271