Development of very low-power PlaS-type plasma thrusters

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


DOI: 10.34759/vst-2021-1-74-85

Аuthors

Kaplin M. A.*, Mitrofanova O. A.*, Bernikova M. Y.*

Experimental Design Bureau “Fakel”, 181, Moskovsky av, Kaliningrad, 236001, Russia

*e-mail: info@fakel-russia.com

Abstract

The article presents an overview and current development status at the EDB Fakel of prospective PlaS-10 and PlaS-10S very low-power plasma thrusters to be applied as a part of small spacecraft.

The study of the world technical level of plasma thruster development was performed. General requirements defining competiveness and high commercialization potential of the thrusters, being developed at the EDB Fakel on the world space market were set forth. The article recounts a brief chronology of the design stages, demonstrates experimental results of the thruster laboratory prototype testing, and recounts further tasks to be fulfilled on this project.

Perspective spaceflight tasks require from small spacecraft an autonomous execution of orbit maneuvers both in the near-Earth and in interplanetary space, for which a low power propulsion system, capable of functioning under conditions of the small spacecraft onboard power supply deficit (up to 100 W) is necessary. The super low power plasma thrusters can fill the empty niche [1] of the small spacecraft movement control systems, and provide the small spacecraft of potential customer with high values of the total thrust impulse for orbital maneuvers performing.

To secure the EDB Fakel leading position at the small spacecraft world market, scientific and research works on developing PlaS-10 and PlaS-10S competitive plasma thrusters of very low-power and enhanced thrust efficiency, based on brand new technical solutions, were initiated. PlaS-10 and PlaS-10S thrusters are the result of the previously developed PlaS-type thrusters concept adaptation at EDB Fakel for very low-power applications [2]. While the PlaS-10 and PlaS-10S thrusters developing the primary efforts are aimed at ensuring the key parameters of these products such as a very low discharge power and high thrust efficiency. The standard size type of the products being developed is the mean diameter of their discharge chambers, which is equal to 10 mm. The PlaS-10 thruster is based on an inner cylindrical anode, and contains a low flow rate hollow cathode-compensator previously developed by EDB Fakel, characterized by relatively high (as applied to a small spacecraft) energetic and mass and size parameters. With the purpose to further improving integral and mass and size parameters of the product, an option of the PlaS-10S structure, employing newly developed thermo-emission cathode-compensator with directly heated filament emitter, requiring less electric power for its functioning, was developed. Besides, the external cylindrical anode was implemented to determine experimentally the best anode configuration in the PlaS-10S thruster.

The small spacecraft of the nearest future based on PlaS-10 and PlaS-10S super low power plasma thrusters will be able to accomplish all types of potential flight tasks, requiring high values of the total thrust impulse available onboard a small spacecraft. These tasks may range from maintaining relative position of a small spacecraft as a part of strict formation of low-orbit multi-satellite systems to accomplishing the exploratory small spacecraft flights into deep space. The high potential of modernization herewith, encumbered into the thruster structure at the stage of development, defines the possibility of thrusters’ thrust and energy characteristics enhancing with the course of time, which is the key factor capable of ensuring the high level of the PlaS-10 and PlaS-10S competiveness supporting in the future.

Keywords:

thruster, plasma thruster, plasma accelerator, very low-power, super low size, small spacecraft, CubeSat

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