EP-4739913-A1 - HALL THRUSTER WITH ELECTRICAL ISOLATION

Abstract

A Hall thruster includes a thruster chassis that defines an axial centerline, radially inner and outer magnetic poles, an annular channel that includes a discharge region between the radially inner and outer magnetic poles, a cathode and an anode, and an electrical power source that has a first terminal electrically connected with the anode and a second terminal electrically connected with the cathode and electrically connected with the discharge region. The thruster chassis is electrically isolated from the anode, the cathode, and the discharge region.

Inventors

• TRESCOTT, Jakob

Assignees

• Aerojet Rocketdyne, Inc.

Dates

Publication Date

20260513

Application Date

20230707

Claims (6)

1. 1. A Hall thruster comprising: a thruster chassis defining an axial centerline; radially inner and outer magnetic poles; an annular channel including a discharge region between the radially inner and outer magnetic poles; a cathode and an anode; and an electrical power source having a first terminal electrically connected with the anode and a second terminal electrically connected with the cathode and electrically connected with the discharge region, the thruster chassis being electrically isolated from the anode, the cathode, and the discharge region.
2. 2. The Hall thruster as recited in claim 1 , wherein the radially inner and outer magnetic poles include thereon, respectively, first and second electrically conductive pole covers that are electrically connected with the second terminal such that the second terminal is electrically connected with the discharge region.
3. 3. The Hall thruster as recited in claim 2, including a first pole insulator axially disposed between the radially inner magnetic pole and the first electrically conductive pole cover, and a second pole insulator axially disposed between the radially outer magnetic pole and the second electrically conductive pole cover.
4. 4. The Hall thruster as recited in claim 1, including at least one magnet magnetically coupled with the radially inner and radially outer magnetic poles to generate a magnetic field across the discharge region.
5. 5. The Hall thruster as recited in claim 1, wherein the cathode is circumscribed by the annular channel.
6. 6. A vehicle comprising: at least one Hall thruster including a thruster chassis defining an axial centerline, radially inner and outer magnetic poles, an annular channel including a discharge region between the radially inner and outer magnetic poles, a cathode and an anode, and an electrical power source having a first terminal electrically connected with the anode and a second terminal electrically connected with the cathode and electrically connected with the discharge region, the thruster chassis being electrically isolated from the anode, the cathode, and the discharge region.

Description

HALL THRUSTER WITH ELECTRICAL ISOLATION BACKGROUND [0001] Ion accelerators with closed electron drift are also known as Hall-effect thrusters or Hall thrusters. Hall thrusters can be used on space vehicles for propulsion, stationkeeping, orbit changes, or counteracting drag, for example. Hall thrusters generate thrust by supplying a gas to an annular channel. The annular channel has a closed end with an anode and an open end through which the gas is discharged. A cathode introduces free electrons into the area of the open end or into the plume. The electrons in the area of the open end are induced to drift circumferentially in the annular channel by a generally radially extending magnetic field in combination with a longitudinal electric field, but the electrons eventually migrate to the anode. The electrons collide with the gas atoms to create ions. The longitudinal electric field accelerates the ions from the open end of the annular channel to generate a reaction force that produces thrust. In general, Hall thrusters come in wide range of discharge power configurations. SUMMARY [0002] A Hall thruster according to an example of the present disclosure includes a thruster chassis that defines an axial centerline, radially inner and outer magnetic poles, an annular channel that includes a discharge region between the radially inner and outer magnetic poles, a cathode, an anode, and an electrical power source that has a first terminal electrically connected with the anode and a second terminal electrically connected with the cathode and electrically connected with the discharge region. The thruster chassis is electrically isolated from the anode, the cathode, and the discharge region. [0003] In a further embodiment of any of the foregoing embodiments, the radially inner and outer magnetic poles include thereon, respectively, first and second electrically conductive pole covers that are electrically connected with the second terminal such that the second terminal is electrically connected with the discharge region. [0004] In a further embodiment of any of the foregoing embodiments, a first pole insulator axially disposed between the radially inner magnetic pole and the first electrically conductive pole cover, and a second pole insulator axially disposed between the radially outer magnetic pole and the second electrically conductive pole cover. [0005] In a further embodiment of any of the foregoing embodiments, at least one magnet magnetically coupled with the radially inner and radially outer magnetic poles to generate a magnetic field across the discharge region. [0006] In a further embodiment of any of the foregoing embodiments, the cathode is circumscribed by the annular channel. [0007] A vehicle according to an example of the present disclosure includes at least one Hall thruster that has a thruster chassis that defines an axial centerline, radially inner and outer magnetic poles, an annular channel that includes a discharge region between the radially inner and outer magnetic poles, a cathode, an anode, and an electrical power source that has a first terminal electrically connected with the anode and a second terminal electrically connected with the cathode and electrically connected with the discharge region. The thruster chassis is electrically isolated from the anode, the cathode, and the discharge region. [0008] The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof. BRIEF DESCRIPTION OF THE DRAWINGS [0009] The various features and advantages of the present disclosure will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows. [0010] Figure 1 illustrates a vehicle that has one or more Hall thrusters. [0011] Figure 2 illustrates a sectioned view of a Hall thruster with electrical isolation. [0012] In this disclosure, like reference numerals designate like elements where appropriate and reference numerals with the addition of one-hundred or multiples thereof designate modified elements that are understood to incorporate the same features and benefits of the corresponding elements. Terms such as “first” and “second” used herein are to differentiate that there are two architecturally distinct components or features. Furthermore, the terms “first” and “second” are interchangeable in that a first component or feature could alternatively be termed as the second component or feature, and vice versa. DETAILED DESCRIPTION [0013] Figure 1 schematically illustrates an aerospace vehicle 20, such as but not limited to, a satellite. The vehicle 20 includes a vehicle body 22 and one or more Hall thrusters 24 attached on the body 22. For example, the thrusters 24 may be used for propulsion, station- keeping, orbit changes, and/or counteracting drag. It is to be appreciated that, to the extent that there are c