Sample machine on basis of principle of nitrous oxide mono-component thruster and use method thereof

Abstract

The invention relates to a sample machine on the basis of the principle of a nitrous oxide mono-component thruster and a use method thereof. The invention utilizes the characteristics of the nitrous oxide gas such as no toxicity, no pollution, high catalytic decomposition temperature and capability of self-maintaining decomposition reaction, and applies the nitrous oxide gas in the propulsion field of aerospace micro-satellites. Compared with the existing commonly-used hydrazine mono-component thruster, the invention can effectively reduce the risk and cost of land disposal with a propellant, and also can realize higher specific impulse performance compared with the cold gas thruster. The invention can conduct principle demonstration verification for mono-component thruster adopting the nitrous oxide as the propellant, and provide technical support for research and development of a non-toxic micro-thruster applied in posture control of the micro-satellite.

Description

【Technical field】 [0001] The invention relates to a principle prototype of a nitrous oxide single-component thruster, which can carry out principle demonstration and verification for a single-component thruster using nitrous oxide as a propellant, and is a non-toxic micro-thruster applied to micro-satellite attitude control R&D provides technical support. 【Background technique】 [0002] With the development of modern industrial technology and electronic technology, there has been an upsurge in the development of micro-spacecraft in the world aerospace industry. Microsatellites have many advantages such as small size, light weight, flexible launch, fast response, short development cycle, high functional density ratio and high cost performance, and are widely used in communication, navigation, reconnaissance, remote sensing, earth environment monitoring and meteorology. The prospects are very bright. The development of micro-satellite technology is of great significance to m...

AI Technical Summary

Problems solved by technology

However, electric propulsion is largely limited by the power of the power supply. The energy demand of electrostatic and electromagnetic propulsion (greater than 100W) is much greater than the energy supply of micro-spacecraft (generally less than 50W); and the power range is more suitable for the PPT of micro-spacecraft And FEEP has the problem of plume pollution again, and the PPT efficiency is very low (5%-15%), FEEP then needs very high voltage

The traditional chemical bicomponent propulsion system is technically difficult and expensive to apply to small satellites by reducing the size, and the propellant is usually toxic and flammable, and it will also encounter problems such as reduced combustion efficiency after size reduction, nozzle or nozzle A series of problems such as easy blockage of the injector, difficulty in precise control of impulse, pollution caused by incomplete combustion, etc.

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