A structure of a swirling micro gas hydrogen oxygen thruster

Abstract

A swirl-type miniature gas hydrogen-oxygen thruster structure, comprising: a hydrogen pipe, an oxygen pipe, an igniter, an igniter base, a nozzle, a combustion chamber, a swirler, and an injector. The injector, the swirler, the combustion chamber and the nozzle are connected in sequence, and the right end of the swirler is provided with a sinking groove, and the sinking groove is used to swirl the oxygen ejected from the oxygen flow channel to form an initial swirl field, and the present invention The swirl ratio ranges from 0.6 to 1.2. The invention realizes rapid mixing of oxygen combustion after injection through structural design and flow field organization, ensuring stable combustion; and effectively cooling the wall surface of the combustion chamber by means of the swirling flow field formed by oxygen flow to ensure safe operation of the thruster.

Description

Technical field [0001] The present invention relates to a swirling microelectric hydrogen oxygen thrust structure, which belongs to the field of thrust. Background technique [0002] Water-based propulsion has the advantages of high-binding, non-polluting, compatible with space life insurance systems, is the frontier and hotspots in the field of space promotion technology, which has great development potential. In a micro-nano-star system using water-based advancement techniques, small (micro) gas hydrogen oxide thrust is an important power device. Its design relates to key issues such as thermal protection in small scale combustion and high temperature conditions, but related research results are limited, and it is still difficult to support all kinds of technical needs. [0003] In a typical microastrian star in the track, the hydrogen oxygen used in the small (micro) thrust is all from the online electrolysis of water, so the oxygen (chemical) combustion (material) mix ratio i...

AI Technical Summary

Problems solved by technology

This causes the thruster to work for a long time in a high-temperature environment formed by equivalent combustion, which brings great challenges to the thermal protection and related structural design of the thruster

[0004] On the other hand, the output power of small (micro) thrusters is low, and the flow rate of oxygen combustion is small. How to achieve rapid mixing in a thrust chamber with limited space and ensure the stability of micro-scale combustion is also the key to thruster design.

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