Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
  • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
  • F03H1/00—Using plasma to produce a reactive propulsive thrust
  • F03H1/0037—Electrostatic ion thrusters
  • F03H1/0062—Electrostatic ion thrusters grid-less with an applied magnetic field
  • F03H1/0075—Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift

Definitions

• the present invention relates to a system for "shaping" the magnetic field in an ion accelerator with closed drift of electrons, i.e., a system for controlling the contour of the magnetic field lines and the strength of the magnetic field in a direction longitudinally of the accelerator, particularly in the area of the ion exit end.
• Ion accelerators with closed electron drift also known as “Hall effect thrusters” (HETs) have been used as a source of directed ions for plasma assisted manufacturing and for spacecraft propulsion.
• HETs Hydrostatic thrusters
• HETs generate thrust by supplying a propellant gas to an annular gas discharge area. Such area has a closed end which includes an anode and an open end through which the gas is discharged. Free electrons are introduced into the area of the exit end from a cathode. The electrons are induced to drift circumferentially in the annular discharge area by a generally radially extending magnetic field in combination with a longitudinal electric field. The electrons collide with the propellant gas atoms, creating ions which are accelerated outward due to the longitudinal electric field. Reaction force is thereby generated to propel the spacecraft.
• Concentration of the magnetic field at the upstream end of the channel therefore should be expected to concentrate ion production further upstream, thereby decreasing the electrical efficiency.
• Morozov et al. achieved different profiles for the radial magnetic field by controlling the current to coils of separate electromagnets.
• other ways to affect the profile of the magnetic field are configuring the physical parameters of magnetic-permeable elements in the magnetic path (such as positioning and concentrating magnetic-permeable elements at the exit end of the accelerator), and by magnetic "screening" or shunts which can be interposed between the source(s) of the magnetic field and areas where less field strength is desired, such as near the anode.
• Gavryushin and Kim describe altering the longitudinal gradient of the magnetic field intensity by varying the degree of screening of the accelerator channel. Their conclusion was that magnetic field characteristics in the accelerator channel have a significant impact on the divergence of the ion plasma stream.
• the present invention provides an improved system for magnetic flux shaping in an ion accelerator with closed electron drift (Hall effect thruster or HET).
• a specially designed magnetic shunt called a "flux bypass cage” is provided encircling the anode region and/or annular gas distribution area of the thruster at both the inside cylindrical wall and outside cylindrical wall.
• the circumferential sides of the flux bypass cage are connected behind the anode. Initially, the cage was formed by a solid walled, U-shaped cross section body of revolution, with the inner and outer sides encompassing substantially all of the anode region of the thruster.
• the flux cage has large openings in the inner and outer circumferential sides.
• the open areas can constitute the major portion of both the outer and inner circumferential sides, hence the term "cage.”
• the flux bypass cage then resembles circumferentially spaced, longitudinally extending side bars connecting rings at the closed end (behind the anode) and rings at the exit end.
• electromagnets can have fewer ampere-turns, as well as lighter cores and structural supports, and the reduction in weight lessens structural support requirements for the thruster itself.
• lighter magnets can be used.
• Another feature of the cage design is that it gives the designer control over the shape of the magnetic field vectors in the ion discharge area. For example, a solid walled shunt can create lines of equipotential at steep angles relative to the centerline of the discharge area. The result is that the ion beam can be "over focused," i.e., have ions at the inner and outer sides directed more toward the mid-channel centerline than is desired for greatest efficiency.
• the magnet poles at the exit end of the HET are coated with insulative material, which further enhances the magnetic field shaping for greater efficiency and longer life.
• FIGURE 1 is a somewhat diagrammatic, top, exit end perspective of an ion accelerator with closed electron drift of a representative type with which the present invention is concerned;
• FIGURE 2 is a somewhat diagrammatic longitudinal section along line 2—2 of FIGURE 1;
• FIGURE 3 is a graph illustrating the effect of a flux bypass component on the magnetic field profile in an accelerator of the type with which the present invention is concerned;
• FIGURE 4 is an enlarged, diagrammatic, fragmentary section of the ion exit end of an accelerator of the type with which the present invention is concerned;
• FIGURE 5 A is a top, rear perspective of a first embodiment of a flux bypass cage in accordance with the present invention for use in an ion accelerator with closed drift of electrons;
• FIGURE 5B is a top, rear perspective of a second embodiment of a flux bypass cage in accordance with the present invention for use in an ion accelerator with closed drift of electrons;
• FIGURE 5C is a top, rear perspective of a third embodiment of a flux bypass cage in accordance with the present invention for use in an ion accelerator with closed drift of electrons;
• FIGURE 5D is a top, rear perspective of a fourth embodiment of a flux bypass cage in accordance with the present invention for use in an ion accelerator with closed drift of electrons;
• FIGURE 6 is a very diagrammatic partial sectional view of an accelerator having a flux bypass cage in accordance with the present invention.
• FIGURE 7 is a diagrammatic partial section of an accelerator of the type with which the present invention is concerned illustrating magnetic field lines and paths;
• FIGURE 8 is a graph illustrating the effects of different bypass components on the magnetic filed strength and profile in a ion accelerator with closed drift of electrons;
• FIGURE 9 is a graph illustrating magnetic field vector angles for different bypass components in an ion accelerator with closed drift of electrons
• FIGURE 10 is a graph illustrating the effects of different bypass components on the magnetic field strength and profile in an ion accelerator with closed drift of electrons.
• FIGURES 11, 12, and 13 are corresponding diagrammatic, fragmentary, sectional views of an accelerator of the type with which the present invention is concerned illustrating magnetic and electric field lines and paths.
• FIGURE 1 illustrates a representative Hall effect thruster (HET) of the type with which the present invention is concerned as it may be configured for spacecraft propulsion.
• HET 10 is carried by a spacecraft-attached mounting bracket 11. Few details of the HET are visible from the exterior, although the electron-emitting cathode 12, exit end 14 of the annular discharge chamber or area 16 and outer electromagnets 18 are seen in this view.
• propulsion is achieved by ions accelerated outward, toward the viewer and to the right as viewed in FIGURE 1 , from the annular discharge area 16.
• the endless annular ion formation and discharge area 16 is formed between an outer ceramic ring 20 and an inner ceramic ring 22.
• the ceramic is electrically insulative, and sturdy, light, and erosion-resistant. It is desirable to create an essentially radially-directed magnetic field in the discharge area, between an outer ferromagnetic pole piece 24 and an inner ferromagnetic pole piece 26. In the illustrated embodiment, this is achieved by the outer electromagnets 18 having windings 28 on bobbins 30 with internal ferromagnetic cores 32. At the exit end of the accelerator, the cores 32 are magnetically coupled to the outer pole piece 24.
• the cores 32 are magnetically coupled to a ferromagnetic backplate 34 which is magnetically coupled to a ferromagnetic center core or stem 36.
• Stem 36 is magnetically coupled to the inner pole 26.
• Structural support is provided by an outer structural body member 39 of insulative and nonmagnetic material bridging between the outer ceramic ring 20 and outer pole 24 at one end and the backplate 34 at the other end.
• a similar inner structural body member 40 extends generally between the inner ring 22 and backplate 34.
• a Belleville spring 41 is interposed between the back ends of the structural members 39 and 40 and the backplate 34, primarily to allow for thermal expansion and contraction of the overall thruster frame.
• the cathode 12, shown diagrammatically in FIGURE 2 is electrically coupled to the accelerator anode 42 which is located upstream of the exit end portion of the annular gas discharge area 16 defined between the outer and inner ceramic rings 20 and 22.
• the electric potential between the cathode 12 and anode 42 is achieved by power supply and conditioning electronics 44, with the potential conveyed to the anode by way of one or more electrically conductive rods 46 extending through the backplate 34 of the HET 10.
• the anode includes electrically conductive inner and outer walls 48 and 50 and an annular protruding portion 52 between the inner and outer walls. The tip of the protruding portion extends downstream close to the upstream edges of the exit rings 20 and 22.
• the rear of the anode has one or more gas distribution chambers 54.
• Propellant gas such as xenon
• a gas supply system 56 is fed to the chambers 54 through one or more supply conduits 58.
• a series of small apertures are provided in a baffle between the fore and aft gas distribution chambers, and between the forward chamber and a series of generally radially extending gas supply apertures 60 for flow outward along the opposite sides of the protruding portion 52 of the anode toward the discharge area 16.
• one more magnetically permeable element is provided, a specially designed flux bypass component 61 having circumferential sides inside the inner anode wall 48 and outside the outer anode wall 50, as well as a rear portion or web behind the anode 42 to connect the inner and outer sides of the bypass component.
• electrons from the cathode 12 are drawn toward the discharge area 16 by the difference in electrical potential between the cathode and the anode 42.
• the electrons collide with atoms of the propellant gas, forming ions and secondary electrons.
• the secondary electrons continue toward the anode, and the ions are accelerated in a beam directed generally outward from the discharge area, creating a reaction force which may be used to accelerate a spacecraft.
• This drift arising from a combination of crossed electric and magnetic fields. This drift is perpendicular to the direction of the electric field and perpendicular to the magnetic field. Since the electric field extends longitudinally and the magnetic field extends radially, the drift is induced in a generally circumferential direction in the annular discharge area 16.
• the electron current due to this drift is called the Hall current and is given by
• E x B — jh qn e _ 2 , where n e is the electron density, E is the electric field vector and
• B is the magnetic field vector.
• the electric field for this device is j ⁇ generally perpendicular to the magnetic field. This arises from the mobility of electrons being different in the directions parallel vs. perpendicular to the magnetic field. Parallel electron motion is unimpeded save for collisions and electric field forces. Perpendicular motion is limited to a cyclotron orbit deflected by infrequent collisions.
• curves defining the direction of the magnetic field approximate equipotential contours.
• the electric field is effectively perpendicular to the magnetic field in Hall accelerators.
• the ion gyro radius is larger by the ratio of the ion mass to electron mass, a factor of several thousand. Hence, the radius of curvature of ions is large compared to the device dimensions and ions are accelerated away from the anode relatively unaffected by the magnetic field.
• the magnetic field shapes the electric potential which in turn affects the acceleration of particles.
• a concave (upstream) and convex (downstream) shape has lens-like properties that focus and defocus the ion beam respectively. More specifically, ions tend to be accelerated in a direction perpendicular to a tangent of a line of equal potential. If this line is convex as viewed from upstream to downstream, ions are accelerated toward the center of the discharge area and a focusing effect occurs. With such focusing properties, this feature of the magnetic system is called a plasma lens.
• maximum can be considered to be the location of ion formation. See, for example, Belan et al.,
• the general idea of the present invention is that ion formation and discharge originate on a fixed magnetic field line or curve, which also approximates a line or curve of equipotential, and that by moving and shaping this curve the ion formation and acceleration location (and direction) can be manipulated.
• a thruster of the general design shown in FIGURES 1 and 2, but without the flux bypass component 61 was operated with different center magnet pole shapes and positions. By moving the center magnet pole downstream with respect to the outer pole, it was found that the location of erosion of the exit rings 20 and 22 moved downstream. This confirmed the hypothesis that the insulator erosion location could be moved by moving the magnetic field lines.
• the magnetic field lines between the magnetic poles were found to have an average angle which aims ions toward the centerline and toward the inner insulator ring, verified by the location of erosion of the inner insulator ring as compared to the location of erosion of the outer insulator ring.
• By adding another electromagnet coil around the center stem or core 36 it was found that the magnetic field could be adjusted to eliminate the tilt. This was confirmed by short duration tests showing that the erosion pattern of the inner and outer insulators was made even in the axial direction when the center coil was used. Current requirements for the electromagnets were kept the same by keeping the same aggregate number of ampere-turns for all of the electromagnets.
• the thruster can operate for longer periods before it erodes through the magnetic poles.
• the net result of the field manipulation was that it increased the life of the thruster by a factor of two or more. More specifically, tests were conducted for an HET of the general design shown in FIGURES 1 and 2, having a mid-channel radius as measured from the centerline A of 41 mm and a radial width ⁇ R between the exit rings of 12 mm.
• the axial length of the insulator rings 20 and 22 along their facing surfaces was 12 mm, including the outer beveled portion, and the radial width of each insulator ring was 6 mm at a location aligned with the adjacent magnet pole piece.
• the ratio of ampere- turns for the four outer coils and the center coil was as given above, with sufficient current to achieve a maximum field strength of about 690 Gauss as measured along the exposed, outer longitudinal side of the inner insulator ring 22.
• the power supply and conditioning electronics provided a potential of 350 volts, 1.7 kilowatts, between the cathode 12 and anode 42.
• Xenon gas was supplied through the hollow anode at a rate of 5.4 mg/sec.
• the magnetic field strength was measured with and without a magnetic shunt 61 having solid sheet cylindrical inner and outer sides surrounding the inner and outer walls 48, 50 of the anode, and projecting part way into the insulator rings 20, 22 as shown in FIGURE 2.
• the back of the shunt was formed by radial ribs with large openings between the ribs to control the reluctance of the path from the outer side of the shunt to the inner side of the shunt.
• Line 63 in FIGURE 3 shows the shape of the magnetic field as measured from the upstream edge of the inner insulator ring with no magnetic flux bypass component in place.
• Line 65 in FIGURE 3 shows the profile of the magnetic field when a flux bypass component with solid sheet inner and outer walls connected together behind the anode was applied. As illustrated in FIGURE 3, the magnetic flux gradient is increased substantially by use of the flux bypass component, and the location of maximum magnetic field strength is moved farther downstream. Erosion of the insulator rings was measured at different stages of the testing.
• FIGURE 4 an enlarged, fragmentary, diagrammatic view of the downstream end portion of the outer insulator ring 20 and adjacent magnetic pole piece 24, outward from the centerline A of the discharge channel 16
• the erosion profile when no bypass component was used is indicated by line 66, which corresponds to ion formation upstream of line 68 in discharge area 16.
• the erosion profile moved to line 70 of FIGURE 4, corresponding to ion formation upstream of line 72, much farther downstream than for the HET with no flux bypass cage.
• a bypass shunt is formed with large openings in either or both of the sides and inner connecting end (behind the anode) of the shunt body to form a cage, as illustrated in FIGURE 5A and FIGURE 5C.
• the cage 61 fits around the anode housing so that the open rings 80 and 82 at the exit end are embedded in the ceramic insulator rings. More specifically, as shown diagrammatically in FIGURE 6, the outer exit end ring 80 is embedded in the inner face of the outer insulator 20, and the inner exit end ring 82 is embedded in the inner face of the inner insulator 22.
• the side openings 81 can encompass much more than the major portion of the circumferential area of the cage.
• strips 84 of magnetically permeable material connect the outer exit end ring and a similar ring 86 at the rear or closed end of the cage.
• Strips 84 are radially aligned with similar strips 88 extending between the inner exit ring 82 and a corresponding ring 90 at the opposite end of the cage.
• the strips can be disposed at 45° from the four outer electromagnets to allow more flux to pass through the open sides of the cage.
• the magnetic path between the outer rings and the inner rings is completed by short radial spokes 92 extending between rings 86 and 90 at the closed end of the cage, behind the anode.
• the large openings 94 at the closed end allow propellant and power lines to feed directly into the anode.
• four strips 84, four strips 88, and four ribs or spokes 92 are shown, larger numbers can be used, preferably with uniform spacing, as illustrated in FIGURES 5B and 5D, to achieve a desired reluctance of the magnetic path defined by the cage.
• reluctance of the rear portion of the cage is controlled by the width of an annular gap 95 between the rear end rings 86 and 90 which have a greater radial dimension than the corresponding rings of the embodiments of FIGURES 5 A and 5B. Nevertheless, the inner and outer rings are magnetically coupled across the gap.
• the open cage design versus the solid wall bypass is that it reduces the ampere-turn requirements and the thruster weight.
• the first flux path 96 shows magnetic flux lines crossing the radial gap between the magnet poles 24 and 26.
• the second flux path 98 connects the inner pole 26 to the inner corner of the flux bypass cage 61 and from the outer corner of the bypass cage to the outer pole 24.
• the third path 100 connects to the middle of the flux bypass from the inner and outer magnet structure.
• the weight and ampere-turn savings with the open cage design are achieved by increasing the average reluctance of paths 98 and 100 which increases the percentage of the total flux passing across path 96. Compared to a solid wall screen which encloses the anode and the mid- stem, the predicted flux through path 100 is 30-40% less and through path 98 is 15-25% less.
• FIGURE 8 shows the field strength in the mid-channel of the discharge area 16 for a solid flux bypass component (line 99) and one version of the open cage design (line 101).
• the abscissa in FIGURE 8 is the axial distance along the outer insulator ring 20. Zero is taken as the point farthest upstream along the insulator. In each instance, erosion of the insulator began at about 4.5 mm from the upstream edge. For the open cage design, this corresponds to a magnetic field strength at mid-channel of about 0.85 of the maximum, i.e., 0.85 B max . Also, the location of the mid-channel B max curve is downstream of the magnet pole pieces in each instance. The measurements show that for a given number of ampere-turns the field strength is about 15%) higher in the mid-channel with the open cage design because a larger percentage of the total flux passes across the radial gap between the poles. Reduction in the total flux required is particularly advantageous for spacecraft applications where minimum mass is important. The ferromagnetic conductor and electromagnetic coil weight are driven by the flux capacity needs as opposed to structural support requirements. Therefore, any reduction in total flux results in a significant weight savings.
• FIGURE 9 shows the angle changes achieved at the outer insulator ring 20 for a completely solid sidewalls and essentially open back cage (line 103) and one with openings in the sides as shown in FIGURE 5 A (line 105).
• the physical parameters of the thruster were the same as those described above with reference to FIGURE 8.
• the x-axis dimension is the distance along the outer insulator ring. Zero is taken as the point farthest upstream along the insulator.
• the angle has been decreased by 50% along the outer insulator ring.
• the point at which the field lines have no axial component has been moved downstream by approximately 1 mm.
• Adjusting the magnetic field shape controls the plasma dynamics and insulator erosion, particularly the convergence and divergence of the ion stream.
• the shape of the field lines strongly influences the shape of the equipotentials and therefore the location of formation of ions and the direction of acceleration.
• the proper field vector angle along the insulator rings will direct the ions away from the walls and reduce erosion. Therefore, control over this parameter allows one to increase the life of the thruster.
• the shape of the field lines can also be controlled by modifying the shape of the exit end rings 80 and 82 and adjusting -R, the radial distance between the insulator rings.
• Electric potentials are set by boundary values and gradients are controlled by the motion of electrons along and across the magnetic field lines.
• the power supply sets the difference between the anode and cathode potentials.
• electric potential differences are small along magnetic lines of force. The small potential differences correspond to the relatively free motion of electrons in the direction of a magnetic field line.
• electric potential gradients are governed by electron mobility. Because electron mobility across field lines is low, high electric potentials develop across magnetic field lines to push electrons toward the anode.
• the best mode for the accelerator in accordance with the present invention uses a magnetic field at mid- channel diameter that peaks downstream of the magnetic pole face, preferably by 1 to 10 mm.
• the pole face may be insulated by a variety of materials.
• Using a plasma sprayed nickel coating on the ferromagnetic pole enables excellent adhesion of a plasma sprayed aluminum oxide insulating coating of a thickness of about 0.5 mm.
• the coating rather than a separate sheet of insulating material improves the thermal radiation from the magnetic pole piece, which is highly desirable for spacecraft propulsion applications.
• operation of the improved accelerator consists of achieving a high thrust efficiency and at the same time a long operating life.
• FIGURE 10 shows the strength of the magnetic field along a line at a mid-channel of the discharge area between the exit rings.
• Magnetic field calculations are performed with conventional computer automated design tools such as EMAG by Engineering Mechanics Research Center Corporation. This is a finite element solver that provides close agreement with measured magnetic fields. These calculations use the physical and operational thruster parameters described with reference to FIGURE 8.
• the points labeled 1, 2, and 3 in FIGURE 10 are in order: the maximum magnetic field strength at mid-channel, B max , for a magnetic system with no flux bypass (point 1); with a solid flux bypass (point 2); and with a cage flux bypass (point 3). These points indicate specific flux lines on the two-dimensional magnetic field calculations for FIGURE 11 which represents no flux bypass, FIGURE 12 which represents a flux bypass component with solid sides, and FIGURE 13 which represents a flux bypass component with openings in the sides.
• the 0.85 B max location is shifted downstream compared to the case without a flux bypass cage.
• the magnetic flux line passing through 0.85 B max is experimentally determined to correspond to the beginning of the erosive part of the discharge, i.e., the most upstream location of insulator erosion.
• moving the location of this strength of magnetic field has been shown to change the location of the erosive portion of the discharge. Comparing the mid-channel, axial location of points 4 and 5, we see that by using a solid flux bypass cage (FIGURE 12), the erosive part of the discharge may be moved downstream.
• the axial location of point 5 may be adjusted by changing the axial position of the flux bypass cage.
• the shape or contour of the magnetic field lines affects the focusing of the plasma lens. This focusing has a primary effect on the efficiency.
• the magnetic field line labeled 4 has a radius of curvature of approximately 80 mm. This is the 0.85 B max location.
• the radius of curvature is approximately 20 mm on the magnetic field line labeled 5 (0.85 B max ).
• the radius of curvature of field line 6 (0.85 B max ) is approximately 40 mm.
• field line 6 in FIGURE 13 intersects the insulator walls at the location which effectively becomes a corner dividing eroded from uneroded insulator.
• the focusing properties of the magnetic lens can be changed without significant relocation of the erosion corner. Adjusting the aggregate cross sectional area of the radial spokes at the rear of the cage (behind the anode) changes the amount of flux bypassing the anode region and affects the curvature of the field line labeled 6 in FIGURE 13.
• the degree of plume divergence may be determined. For accelerators with plasma lens characteristics like those shown in FIGURE 12, we find higher divergence than for lens characteristics of FIGURE 13 for a 350 V discharge. Thus, the longer focal length of the magnetic lens in FIGURE 13 provides improved plume properties from the standpoint of divergence angle.
• the peak magnetic field strength at mid-channel is also affected by the amount of flux bypassing the anode region.
• the curves in FIGURE 10 represent mid-channel magnetic field strengths for a coercive force of 1,000 ampere-turns. Assuming the magnetic field in the primary magnetic circuit does not saturate the permeable elements, the maximum field strength for each case is approximately proportional to the coercive force. To increase the strength of point 2 to equal point 1 , the coercive force for the solid shunt configuration must be increased by the ratio of the magnetic field of point 1 over point 2 or 42%.
• the flux bypass cage requires only a 20% increase in coercive force to achieve the same peak magnetic field as point 1.
• the reduction in the number of ampere-turns for an accelerator used as a spacecraft thruster can have a useful decrease in weight of the magnetic system.
• the cage design is also advantageous from a thermal standpoint.
• One of the drawbacks of shields which are separate from but enclose the anode and mid-stem is that they inhibit radiative cooling of the anode. Radiative cooling decreases the heat conduction to the spacecraft and allows the mid-stem to operate at cooler temperatures which increase its flux capacity.
• the reduced ampere-turn requirement for the cage type flux bypass reduces the ohmic power dissipated in the coils.
• one important parameter is the angle i between a radial line at the upstream edge of the inner magnetic pole piece 26 and a line from the inner upstream corner of the pole piece to the adjacent corner of the bypass cage.
• Another aspect is the amount of open area in the sides of the cage. The best results to date have been obtained when the side openings encompass the major portion of the circumferential area, permitting flux to pass through the openings and reducing the total coercive force required.

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• 1999
  • 1999-06-03 DE DE69902589T patent/DE69902589T2/de not_active Expired - Lifetime
  • 1999-06-03 EP EP99931754A patent/EP1082540B1/en not_active Expired - Lifetime
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  • 1999-06-03 WO PCT/US1999/012402 patent/WO1999063221A2/en active IP Right Grant
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