A blade-type porous material emitter array miniature field emission electric thruster

Abstract

The invention discloses a blade-type porous material emitter array miniature field emission electric thruster, which comprises a neutralizer connected to each other and a thruster main body, and the thruster main body includes a gate, an insulating The bracket and the propellant storage chamber, the insulating bracket has a frame structure, and a blade-type emitter array matched with the grid is arranged inside the insulating bracket, and a matching heater and a heater are arranged below the emitter array The propellant, the propellant and the heater are all located in the propellant storage chamber, so as to realize the miniaturization of the field emission electric thruster structure and meet the requirements of the micro-satellite with a weight below 50kg.

Description

technical field [0001] The invention relates to the technical field of satellite launch, in particular to a blade type porous material emitter array miniature field emission electric thruster. Background technique [0002] At present, micro-satellites with high functional integration have become a reality and are developing very rapidly, especially micro-satellites with a weight of 1-50kg. Due to the short development cycle, low development and launch costs, flexible launch, and difficult detection, micro-satellites can form a "virtual large satellite" in the form of a constellation and form a "virtual large satellite" in the form of a constellation, such as Large-scale remote sensing has been highly valued by countries all over the world, and the number of launches has increased rapidly in recent years. However, most of the microsatellites below 50 kg are not equipped with propulsion systems, and some are equipped with low-performance cold air propulsion systems or single-...

AI Technical Summary

Problems solved by technology

[0006] (1) The current needle-type field emission electric thruster uses a single or multiple emitting needles as the emitter. Due to the small effective emission area, the thrust is small (generally, the thrust generated by a single emitting needle is 20-50μN)

In addition, due to the long launch needle and the need for fine assembly, the size and weight of the thruster are relatively large. It is more difficult to use it for tiny satellites weighing less than 50kg, and it is even more difficult to perform orbit transfers and other occasions that require high thrust.

[0007] (2) Narrow-slit field emission electric thruster adopts narrow-slit emitter, and its effective emission area is larger than that of needle-type field emission electric thruster, so the thrust is large. The heavy weight leads to a large size and weight of the thruster. When used for tiny satellites with a weight of 10-50 kg, there are problems such as weight and size are too large, and it is more difficult to use for satellites below 10 kg.

[0008] In summary, the current field emission electric thruster structure is difficult to miniaturize, and it is difficult to meet the needs of micro-satellites weighing less than 50kg

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