Pinhole array miniature electrostatic electric thruster

Abstract

The invention discloses a pinhole array miniature electrostatic electric thruster. The pinhole array miniature electrostatic electric thruster comprises a neutralizer and a thruster body which are mutually connected, wherein the thruster body sequentially comprises a grid component, a pinhole array component and a propellant storage chamber which are cooperatively connected from top to bottom; the pinhole array component is formed by conveying plates and a pinhole array plate; the conveying plates are arranged on the lower surface of the pinhole array plate; pinhole arrays are uniformly distributed in the pinhole array plate; the grid component consists of an extraction grid, an acceleration grid and an insulation bracket; the extraction grid, the acceleration grid and the pinhole array plate are sequentially connected through the insulation bracket; and coaxial pinholes corresponding to the pinhole arrays are formed in the extraction grid and the acceleration grid; and heaters and the propellant are all located in the propellant storage chamber. The pinhole array miniature electrostatic electric thruster has the advantages that the structure is simple; the size is small; the specific impulse can reach 700-2000 s; the propellant storage function and the conveying function are integrated; the propellant is stored in a pressure-free mode; no movable components exist; and the like. The pinhole array miniature electrostatic electric thruster can be packaged in a chip mode, and can be applied to microsatellites as a standard thrusting module.

Description

technical field [0001] The invention relates to a small-hole array miniature electrostatic electric thruster, which is suitable for tasks such as micro-satellite orbit transfer, attitude control, momentum wheel unloading and atmospheric resistance compensation. Background technique [0002] At present, micro-satellites with high functional integration are developing very rapidly, especially micro-satellites with a weight of 1-10 kg, such as Cubesats. The standard shape of a CubeSat is a cube of 10cm×10cm×10cm, called 1U, with a mass of 1-2kg. According to the functional requirements of the satellite, it can be extended to 2 units (2U) or multiple units to perform remote sensing, communication, Space experiments, formation flight networking and other tasks. 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 larg...

AI Technical Summary

Problems solved by technology

However, conventional satellite propulsion systems, such as chemical propulsion, Hall electric propulsion, and ion electric propulsion, are currently trending towards miniaturization to meet the needs of micro-satellites. However, due to the large number and large size of components such as valves, Storage tanks for storing propellant under pressure are required, the system is relatively complex, the cost is high, the development cycle is long, and miniaturization is very difficult, and it is difficult to adapt to the strict weight, size, price and other restrictions of microsatellites

At present, most of the microsatellites under 10kg are not equipped with propulsion systems, and a few are equipped with micro-air-cooled propulsion systems with low performance such as specific impulse, total impulse, and thrust adjustment capabilities (specific impulse is about 30-90s), and micro-units. Chemical propulsion systems (specific impulse about 210s), micro-bicomponent chemical propulsion systems (specific impulse about 260-300s), etc., greatly limit the mobility, attitude stability and lifespan of micro-satellites

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