Ground based systems and methods for testing reaction thrusters

Patent metadata

Field	Value
Publication number	US-10590919-B2
Application number	US-201415033974-A
Country	US
Kind code	B2
Filing date	Apr 7, 2014
Priority date	Nov 4, 2013
Publication date	Mar 17, 2020
Grant date	Mar 17, 2020

Abstract

System ( 300, 400 ) and methods ( 500 ) for testing a reaction thruster ( 100 ) in a vacuum environment. The methods comprise: disposing the reaction thruster in a vacuum chamber which is at least partially connected to earth ground; removing at least one gas from the vacuum chamber to provide the vacuum environment; operating the reaction thruster so as to create a beam of electrons; and/or electrically isolating the electrons of the beam from at least one electrically conductive surface of the vacuum chamber. The electrical isolation can be achieved by applying an electrical bias voltage to the beam via an electrode. The electrode may comprise a conductive object disposed in the vacuum chamber and/or at least a portion of a vacuum chamber wall. In all cases, the electrode is electrically isolated from a portion of the vacuum chamber that is connected to ground.

First claim

We claim:

1. A method for testing a reaction thruster in a terrestrial vacuum environment, comprising the steps of:
disposing the reaction thruster in a vacuum chamber which is at least partially connected to earth ground and at least partially formed of a conductive material; and
preventing electrons of a beam formed by the reaction thruster from being attracted to at least one electrically conductive surface of the vacuum chamber.

2. The method according to claim 1 , wherein the preventing step comprises applying an electrical bias voltage to the beam.

3. The method according to claim 2 , wherein the electrical bias voltage is applied to the beam using an electrode disposed inside and electrically isolated from the vacuum chamber.

4. The method according to claim 3 , further comprising dynamically adjusting a level of a voltage applied to the electrode during operation of the reaction thruster.

5. The method according to claim 4 , wherein the level is dynamically adjusted based on at least one of a density of neutral gas within the vacuum chamber, a voltage of a cathode of the reaction thruster to the vacuum chamber, a value of a current in plasma flowing from the reaction thruster, and an amount of current collected at the electrode.

6. The method according to claim 1 , wherein the preventing step comprises applying a bias voltage to a downstream end or area of the vacuum chamber such that the downstream end or area has a more positive potential relative to the beam of ions and electrons.

7. The method according to claim 6 , wherein the downstream end of the vacuum chamber is electrically isolated from an upstream end of the vacuum chamber which is connected to the earth ground.

8. The method according to claim 1 , wherein the preventing step comprises disposing a dielectric material adjacent to the electrically conductive surface of the vacuum chamber.

9. The method according to claim 1 , wherein the preventing step comprises disposing a floating material adjacent to the electrically conductive surface of the vacuum chamber.

10. The method according to claim 1 , wherein the reaction thruster comprises a floating ground.

11. The method according to claim 1 , further comprising electrically isolating the electrons or ions of the beam from at least one conductive surface of equipment disposed inside the vacuum chamber that is in electrical contact with the vacuum chamber.

12. A test system, comprising:
a vacuum chamber at least partially formed of a conductive material and comprising at least a first portion electrically connected to earth ground; and
an electrode configured to prevent electrons of a beam created by a reaction thruster from being attracted to at least one electrically conductive surface of the vacuum chamber.

13. The test system according to claim 12 , wherein the electrons are prevented from being attracted to the electrically conductive surface by an application of an electrical bias voltage to the beam.

14. The test system according to claim 12 , wherein the electrode is disposed inside and electrically isolated from the vacuum chamber.

15. The test system according to claim 14 , further comprising a controller configured to facilitate a level adjustment of a voltage applied to the electrode during operation of the reaction thruster.

16. The test system according to claim 15 , wherein the level is dynamically adjusted based on at least one of a density of neutral gas within the vacuum chamber, a voltage of a cathode of the reaction thruster to the vacuum chamber, a value of a current in plasma flowing from the reaction thruster, and an amount of current collected at the electrode.

17. The test system according to claim 11 , wherein the electrode comprises at least a first portion of the vacuum chamber which has a more positive potential relative to the beam of ions and electrons.

18. The test system according to claim 17 , wherein the first portion of the vacuum chamber is electrically isolated from a second portion of the vacuum chamber which is connected to ground.

19. The test system according to claim 11 , further comprising a dielectric material disposed adjacent to the electrically conductive surface of the vacuum chamber.

20. The test system according to claim 11 , further comprising a floating material disposed adjacent to the electrically conductive surface of the vacuum chamber.

Assignees

• Aerojet Rocketdyne Inc

Inventors

• King David Q
• Peterson Peter Y
• Pucci Justin M

Classifications

• B64G2007/005

  Space simulation vacuum chambers · CPC title

• G01L21/30

  by making use of ionisation effects · CPC title

• F03H1/00 Primary

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• F03H1/0075 Primary

  with an annular channel; Hall-effect thrusters with closed electron drift · CPC title

• B64G7/00

  Simulating cosmonautic conditions, e.g. for conditioning crews · CPC title