Hall effect plasma thruster with insulated layered ring assembly
The Hall effect plasma thruster includes a main annular channel for ionization and acceleration that presents an open downstream end, at least one cathode, an annular anode concentric with the main annular channel, a pipe and a manifold for feeding the channel with ionizable gas, and a magnetic circuit for creating a magnetic field in the main annular channel. The main annular channel includes inner and outer annular wall portions delimiting the open end, each of which includes an assembly of juxtaposed conductive or semi-conductive rings in the form of laminations separated by fine layers of insulation.
1. A Hall effect plasma thruster having a main annular channel for ionization and acceleration that presents an open downstream end, at least one cathode, an annular anode concentric with the main annular channel, a pipe and a manifold for feeding the main annular channel with ionizable gas, and a magnetic circuit for creating a magnetic field in said main annular channel, wherein the main annular channel has inner and outer annular wall portions delimiting said open end, each of which comprises an assembly of juxtaposed conductive or semi-conductive rings in the form of laminations separated by fine layers of insulation, each of the fine layers of insulation having a thickness smaller than a thickness of said conductive or semi-conductive rings.
2. The plasma thruster according to claim 1 , wherein each conductive or semi-conductive ring is subdivided into segments arranged as angular sectors and insulated from one another.
3. The plasma thruster according to claim 2 , wherein the segments of each conductive or semi-conductive ring are arranged in a staggered configuration relative to the adjacent conductive or semi-conductive ring segments.
4. The plasma thruster according to claim 3 , wherein:
the fine layers of insulation are arranged on all faces of a conductive or semi-conductive ring with the exception of the face defining a portion of the inside wall of the main annular channel;
the assembly of juxtaposed conductive or semi-conductive rings extends over a length of the inner and outer annular walls in the range 20% to 50% of the total length of the main annular channel;
the conductive or semi-conductive rings are made of graphite;
the fine layers of insulation are made of pyrolytic boron nitride; and
the thickness of the conductive or semi-conductive rings has a value which is of an order of a value of an electron Larmor radius.
5. The plasma thruster according to claim 1 , wherein the fine layers of insulation are arranged on all faces of a conductive or semi-conductive ring with the exception of the face defining a portion of the inside wall of the main annular channel.
6. The plasma thruster according to claim 5 , wherein the fine layers of insulation are made of pyrolytic boron nitride.
7. The plasma thruster according to claim 6 , the fine layers of insulation present thickness in a range of 0.04 millimeter to 0.08 millimeter.
8. The plasma thruster according to claim 1 , wherein the conductive or semi-conductive rings are made of graphite.
9. The plasma thruster according to claim 8 , wherein the conductive or semi-conductive rings present thickness in a range of 0.7 millimeter to 0.9 millimeter.
10. The plasma thruster according to claim 1 , wherein said assembly of juxtaposed conductive or semi-conductive rings extends over a length of the inner and outer annular walls in a range of 20% to 50% of a total length of the main annular channel.
11. The plasma thruster according to claim 1 , wherein the fine layers of insulation are made of pyrolytic boron nitride.
12. The plasma thruster according to claim 1 , wherein the thickness of the conductive or semi-conductive rings has a value which is of the order of the value of an electron Larmor radius.