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Hall effect thruster

A Hall-effect, thruster technology, applied in aircraft, thrust reversers, machines/engines, etc., can solve the problem of not mentioning Hall-effect thrusters

Active Publication Date: 2014-10-08
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION (S N E C M A)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the document does not mention how to make this hall effect thruster operate in high thrust mode and high specific impulse mode

Method used

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Examples

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Embodiment Construction

[0023] Figure 1A and Figure 1B Two different positions of the same Hall effect thruster 1 in the first embodiment are shown. The impeller 1 has an annular channel 2 delimited by inner and outer walls 3 and 4 coaxial around a central axis X, these coaxial walls being made of ceramic material. The annular channel 2 has an open downstream end and a closed upstream end. At its upstream end, the annular channel 2 also has nozzles 10 for injecting propellant gas into the annular channel 2 . The nozzle 10 is connected to a source of propellant gas through an injection circuit 11 comprising a flow rate regulating device 24 . For example, these devices 24 may include pencil valves or thermo-capillaries, which are capillary tubes with heating means that can actively change their own temperature and thus the flow rate through them. Such a flow rate regulator can also be combined with a passive restrictor. The propellant gas may be xenon, which has the advantage of high molecular we...

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Abstract

The invention relates to the field of Hall effect thrusters, and in particular to a thruster (1). The downstream end of the annular channel (2) of the thruster has a variable cross-section so as to be capable of varying the thrust and the specific impulse.

Description

technical field [0001] The present invention relates to the field of Hall effect thrusters. [0002] The present invention more particularly relates to a Hall effect thruster having an annular channel, an anode, an injection circuit, a magnetic circuit and a cathode. The annular passage is defined by inner and outer walls coaxial about a central axis and has an open downstream end and a closed upstream end. The anode is located at the upstream end of the annular channel. The injection circuit is adapted to inject propellant gas, such as xenon, into the annular channel. The magnetic circuit is adapted to generate a magnetic field at the downstream end of the annular channel. The cathode is located outside the downstream end of the annular channel. [0003] In this context, the terms "upstream" and "downstream" are defined relative to the propellant gas along the normal flow direction defined by the central axis of the annular channel. Background technique [0004] Typica...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F03H1/00
CPCF03H1/0075F03H1/0006F03H1/00F03H1/0037B64G1/405F03H1/0068F03H1/0062
Inventor V·M·韦尔乔尔·莫伦
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION (S N E C M A)
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