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Method for controlling the temperature of an electric propulsion system

By determining the reference hot spot in the electric thruster and using magnetic windings for heating, combined with the predefined model, the problem of inaccurate temperature control of the electric thruster and the large size of the heating equipment is solved, and precise and economical temperature control is achieved.

Active Publication Date: 2019-03-15
AIRBUS DEFENSE & SPACE SIMPLIFIED AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the temperature is measured indirectly, resulting in the temperature recorded by the temperature sensor not representing the temperature inside the electric thruster
[0011] On the other hand, since the exact temperature inside the electric thruster is unknown, the electric thruster's heating equipment is oversized, especially to ensure that the electric thruster stays hot enough when it is not operating
Therefore, the heating equipment of such electric thrusters is very energy-intensive

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0057] The invention relates to the temperature control of electric thrusters.

[0058] Electric thrusters are used to equip satellites, which will be sent to stations for their mission purposes, such as in GEO orbit or Low Earth Orbit ("Low Earth Orbit" or LEO).

[0059] In the following description, the Hall effect thruster is considered without limitation. However, it is not excluded to consider other electric thrusters, as long as they include a magnetic circuit, such as magnetic plasma powered thruster (MPD), high efficiency multi-stage plasma (HEMP, the acronym for English "High Efficiency Multistage Plasma") thruster Or Helicon thruster. The Hall-effect propulsion system, referred to as the propeller 1, is shown in perspective and partial cross-sectional views in a single figure, which itself is conventional.

[0060] The propulsion system 1 includes an annular channel called the discharge channel 2, which is defined by an inner wall 3 and an outer wall 4, which are concentr...

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PUM

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Abstract

The invention relates to a method for controlling the temperature of an electric propulsion system (1), said electric propulsion system comprising a discharge channel (2), an anode (40), a cathode (50), an injection system (10) for injecting propellant gas into the discharge channel (2), and a magnetic circuit comprising at least one magnetic winding (20, 30) for generating a magnetic field in thedischarge channel. The method is characterised in that it comprises: a step of determining the temperature at a reference thermal point of the electric propulsion system (1); and, when the determinedtemperature is below a minimum temperature predetermined during a stop phase of the electric propulsion system, a step of heating the electric propulsion system (1) by the Joule effect by applying acurrent to the magnetic circuit.

Description

Technical Field [0001] This invention belongs to the field of space propulsion. More specifically, this invention relates to an electric thruster. [0002] This invention relates to a method for controlling the temperature of an electric thruster. Background Technology [0003] In the field of space propulsion, electric thrusters are increasingly used, particularly for the orientation and orbit control of spacecraft, and more specifically, for the orientation and orbit control of satellites. In fact, the different types of electric thrusters available typically offer higher specific impulse than chemical thrusters, thus helping to reduce propellant consumption for the same maneuvers, thereby increasing satellite lifespan and / or payload. [0004] Among various types of electric thrusters, especially those known as electrostatic thrusters, the propellant fluid is ionized and directly accelerated by an electric field. So-called Hall effect thrusters belong to this category. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01K7/36G01K7/42
CPCF03H1/0031F03H1/0075G01K7/36G01K7/42G01K2205/00G01K2217/00
Owner AIRBUS DEFENSE & SPACE SIMPLIFIED AG