Spiral-flow type miniature gas-hydrogen-oxygen thruster structure

Abstract

A spiral-flow type miniature gas-hydrogen-oxygen thruster structure comprises a hydrogen pipe, an oxygen pipe, an igniter, an igniter base, a spray pipe, a combustion chamber, a cyclone and an injector. The injector, the cyclone, the combustion chamber and the spray pipe are sequentially connected, a settling tank is formed in the right end face of the cyclone, the settling tank is used for enabling oxygen sprayed out of an oxygen flow channel to swirl to form an initial rotational flow field, and the value range of the swirl ratio is 0.6-1.2. Through structural design and flow field organization, oxygen fuel can be rapidly mixed after injection, and stable combustion is guaranteed; and the wall surface of the combustion chamber is effectively cooled by means of a rotational flow field formed by oxygen flowing, so that safe operation of a thruster is guaranteed.

Description

technical field [0001] The invention relates to a structure of a swirling miniature gas-hydrogen-oxygen thruster, which belongs to the technical field of thrusters. Background technique [0002] The water-based propulsion system (water-based propulsion) has the advantages of high specific impulse, no pollution, and good compatibility with the space life support system. It is the frontier and hot spot in the field of space propulsion technology research and has great development potential. In micro-nano-satellite systems using water-based propulsion technology, small (micro) gas-hydrogen-oxygen thrusters are important power devices. Its design involves key issues such as micro-scale combustion and structural thermal protection under high temperature conditions, but the relevant research results are limited, and it is still difficult to support various technical requirements. [0003] In a typical micro-nano-satellite on-orbit application scenario, the gas, hydrogen, and oxyg...

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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