Hydrazine arc thruster ignition system for inhibiting large pressure fluctuation

Abstract

The invention relates to a hydrazine arc thruster ignition system for inhibiting large pressure fluctuation. The hydrazine arc thruster ignition system for inhibiting large pressure fluctuation comprises a diaphragm storage tank (1), a propellant filter (2), a propellant throttling orifice plate (3), a fuel gas generator (4) and an arc thruster (5). According to the system, the problems that the burning pressure of the fuel gas generator is greatly fluctuated due to bubble evolution in a propellant, and the burning pressure is greatly fluctuated due to a heat resistance change before and afterarcing are solved, the times and the amplitude of burning pressure fluctuation of the fuel gas generator can be greatly reduced, and the change of an arc attachment mode during an arc thruster ignition process is avoided, so that the damage on an electrode is reduced, and the service life of a thruster is prolonged.

Description

technical field [0001] The invention relates to an ignition system of a hydrazine arc thruster capable of suppressing large pressure fluctuations, and belongs to the field of electric propulsion ignition systems. Background technique [0002] The hydrazine arc thruster is an electrothermal electric propulsion technology with good development prospects. It is compatible with the mature mono-element propulsion system used on the planet, sharing a set of storage and supply systems, and the specific impulse of the hydrazine arc thruster is much higher than that of a single-unit The component thruster can greatly reduce the consumption and carrying capacity of propellant. Therefore, the hydrazine arc thruster has very obvious advantages as the propulsion power system for maintaining the north-south position of the geosynchronous orbit satellite. Due to the high life requirements of geosynchronous orbit satellites, in order to meet the mission requirements, the hydrazine arc thru...

AI Technical Summary

Problems solved by technology

[0006] The technical problem solved by the invention is: in the current prior art, the hydrazine arc ignition system frequently has large pressure fluctuations caused by air bubbles and fuel pressure fluctuations caused by changes in thermal resistance before and after arcing, which seriously affects the life of the arc thruster and For the application of space missions, a hydrazine arc thruster ignition system that suppresses large fluctuations in pressure is proposed, which greatly reduces the number and magnitude of large fluctuations in combustion pressure during lifetime ignition, thereby increasing the service life of arc thrusters to meet the needs of space missions

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