CN110618443B - Plasma thruster steady-state ion flow field measuring device and measuring method - Google Patents
Plasma thruster steady-state ion flow field measuring device and measuring method Download PDFInfo
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- CN110618443B CN110618443B CN201910791659.6A CN201910791659A CN110618443B CN 110618443 B CN110618443 B CN 110618443B CN 201910791659 A CN201910791659 A CN 201910791659A CN 110618443 B CN110618443 B CN 110618443B
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- G01T1/29—Measurement performed on radiation beams, e.g. position or section of the beam; Measurement of spatial distribution of radiation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
- G01T1/00—Measuring X-radiation, gamma radiation, corpuscular radiation, or cosmic radiation
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Abstract
The embodiment of the invention provides a device and a method for measuring a steady-state ion flow field of a plasma thruster, and belongs to the technical field of steady-state ion flow field measurement. The device comprises a measuring module, a power supply module and a probe assembly, wherein the probe assembly comprises a probe, a probe support and an electric turntable, the probe comprises an insulating shell, an ion receiving electrode, an incident grid and an emergent grid, one end of the insulating shell is open, the incident grid is positioned at the opening of the insulating shell, the emergent grid is positioned in the middle of the inner cavity of the insulating shell, the ion receiving electrode is positioned in the inner cavity of the insulating shell and is far away from one section of the incident grid, an incident hole of the incident grid and an emergent hole of the emergent grid are coaxial, the ion receiving electrode, the incident grid and the emergent grid are mutually insulated, the insulating shell is fixed on the probe support, and the electric turntable is used for driving the probe. The probe of the device rotates around the measuring point to obtain the ion current density distribution function on each azimuth angle at the measuring point and obtain the vector angle of the ion velocity at the same time.
Description
Technical Field
The invention relates to the technical field of steady-state ion flow field measurement, and particularly provides a device and a method for measuring a steady-state ion flow field of a plasma thruster.
Background
The Hall thruster is a very typical plasma electric propulsion device in the international field at present. The plasma thruster generates a reaction thrust by means of a high-speed injected plasma plume, and the working efficiency of the plasma thruster is determined by the distribution characteristics of a steady-state ion flow field in a plume region. Therefore, obtaining the steady-state ion current field distribution of the plume region has important significance for optimizing the performance of the thruster.
Because the plasma thruster has a complicated ionization acceleration process, the ion flow field in the plume region has a very complicated spatial structure. In the ion flow field, it is a technical difficulty in the field to obtain the ion current density distribution and the velocity vector angle thereof at each point. In order to obtain the characteristic information of the ion flow field in the plume region of the thruster, a Faraday probe is usually adopted to measure the ion current in the plume region of the thruster respectively. Chinese patent documents CN105116435A and CN105116436A disclose a method for synchronously measuring an ion flow field by using a Faraday probe array, and the Faraday probe used therein adopts a conventional probe structure design, so that the vector angle distribution of the ion velocity cannot be obtained. In the document "magnetic filtered radar probe for measuring the ion current density profile of a hall crash", the Faraday probe can only be used for measuring the ion current density of the thruster, and the vector angle of the ion velocity cannot be obtained.
Disclosure of Invention
Aiming at the problems in the prior art, the embodiment of the invention provides a device and a method for measuring the steady-state ion flow field of a plasma thruster.
The technical solution of the invention is as follows:
a plasma thruster stable-state ion flow field measuring device comprises a measuring module, a power supply module and a probe assembly, wherein the probe assembly comprises a probe, a probe support and an electric turntable, the probe comprises an insulating shell, an ion receiving electrode, an incident grid and an emergent grid, one end of the insulating shell is opened, the incident grid is positioned at the opening of the insulating shell, the emergent grid is positioned in the middle of an inner cavity of the insulating shell and divides the inner cavity into two sections, the ion receiving electrode is positioned in one section of the inner cavity of the insulating shell, which is far away from the incident grid, an incident hole of the incident grid and an emergent hole of the emergent grid are both positioned on the axis of the inner cavity of the insulating shell, the ion receiving electrode, the incident grid and the emergent grid are mutually insulated, the insulating shell is fixed on the probe support, and the electric turntable is used for driving the probe support to rotate around the incident hole of the incident grid, the power module is used for providing negative bias voltage for the emergent grid to filter electrons, and the measuring module is used for measuring an ion current signal of the ion receiving electrode and a corner signal of the electric turntable.
In an optional embodiment, the distance between the incident hole and the exit hole is 2-3 cm, and the distance between the exit hole and the receiving surface of the ion receiving electrode is 2-4 mm.
In an optional embodiment, the ion receiving electrode is arranged in an insulating manner through an insulating mounting assembly, the ion receiving electrode is of a step structure with a T-shaped cross section, the insulating mounting assembly comprises an insulating ceramic seat and an inner nut, the inner cavity of the insulating ceramic seat is of the step structure matched with the ion receiving electrode, the length of the large-diameter section of the inner cavity is larger than that of the large-diameter section of the ion receiving electrode, the ion receiving electrode is located in the inner cavity of the insulating ceramic seat, the exit grid is located on the end face of the large-diameter end of the inner cavity of the insulating ceramic seat, the small-diameter section of the inner cavity of the insulating ceramic seat is provided with an inner nut mounting groove, and the inner nut is located in the inner nut mounting groove and is in threaded connection with the diameter section of the ion receiving electrode.
In an alternative embodiment, the outer edge of the end face of the ion receiving very large diameter end is provided with a ring of annular protrusions.
In an optional embodiment, the probe support includes the probe mounting hole, the probe mounting hole is the step hole, insulating housing includes first casing and the second casing of butt joint, first casing joint is in the minor diameter section of probe mounting hole, the second casing is installed the major diameter section of probe mounting hole, just the second casing inner chamber is the stair structure, the minimum end of ion reception is located in the first casing, the major end is located the major diameter section of second casing inner chamber, the exit grid is located the step face department of second casing inner chamber, the entrance grid is fixed second casing inner chamber minor diameter section opening part.
In an optional embodiment, the first shell is a hollow cylindrical structure with an open end, the open end of the first shell is provided with a flanging, the first shell is inserted into the small end of the probe mounting hole, the flanging is located on the step surface of the probe mounting hole, two ends of the second shell are open, the large-diameter end of the inner cavity of the second shell is in butt joint with the flanging of the first shell, the insulating ceramic seat is of a stepped cylindrical structure, the small end of the insulating ceramic seat is located in the inner cavity of the first shell, the large end of the insulating ceramic seat is located in the large-diameter section of the inner cavity of the second shell, and the outer step surface of the insulating ceramic seat is attached to the flanging of the first shell.
In an optional embodiment, the second housing is of a stepped cylindrical structure, a gap is formed between the second housing and the large-diameter section of the probe mounting hole, the second housing is fixedly connected with the probe mounting hole through a front end top cover, an inner cavity of the front end top cover is of a stepped structure matched with the outer profile of the second housing, the front end top cover is in threaded connection with the probe mounting hole, an inward flange is arranged at an opening of the small-diameter section of the inner cavity of the front end top cover, the incident grating is clamped in the inward flange, and an insulating ceramic ring is padded at a contact position of the incident grating and the inward flange.
In an optional embodiment, the power supply module includes a bias power supply and a bias power supply line, one end of the bias power supply line is connected to the exit grating, the other end of the bias power supply line is connected to the negative electrode of the bias power supply, and the positive electrode of the bias power supply is grounded.
In an optional embodiment, the measurement module includes a signal line, a power connection line, and a signal acquisition circuit, one end of the signal line is connected to the ion receiving electrode, the other end of the signal line is connected to the input end of the signal acquisition circuit, and the signal acquisition circuit is connected to the negative electrode of the bias power supply through the power connection line.
In an optional embodiment, the plasma thruster steady-state ion flow field measurement device further includes a two-dimensional moving platform, the two-dimensional moving platform includes a z-axis telescopic rod and an X-direction slide rail, the probe support is fixed on the z-axis telescopic rod through the electric turntable, and the z-axis telescopic rod slides along the X-direction slide rail under the action of external force.
A steady state ion flow field measurement method, comprising:
providing negative bias voltage for an emergent grid in the probe assembly through a power supply module in the device to filter electrons;
receiving the ion current of an ion flow field measuring point through an ion receiving electrode in the probe assembly, and driving the probe support to rotate around an incident hole of the incident grid for a preset angle from a preset starting point by the electric turntable during receiving;
meanwhile, measuring an ion current signal of the ion receiving electrode and a corner signal of the electric turntable through a measuring module in the probe assembly so as to determine a functional relation between current intensity and a rotation angle;
and determining the rotation angle corresponding to the maximum value of the ion current intensity according to the functional relation between the current intensity and the rotation angle to obtain the ion velocity vector angle at the measuring point.
In an optional embodiment, the steady-state ion flow field measurement method further includes:
and determining the ion current density at the measuring point according to the current intensity and the diameter of the incident hole of the incident grid.
Compared with the prior art, the invention has the beneficial effects that:
according to the steady-state ion flow field measuring device of the plasma thruster, provided by the embodiment of the invention, the small holes of the incident grid and the emergent grid are coaxially arranged, so that an ion current signal of the ion receiving electrode has selectivity in the ion velocity direction, the probe rotates around the measuring point to obtain an ion current density distribution function in each azimuth angle at the measuring point, and simultaneously obtain a vector angle of the ion velocity; by changing the position of the measuring point of the probe in the plume region, the steady-state ion current density distribution function and the ion velocity vector angle distribution of each point in the whole plume region can be finally obtained. The device can solve the problem that the Faraday probe is insufficient in measurement in the complex plume structure of the plasma thruster, and provides an effective measurement method for researching the steady-state plume structure of the thruster in different modes.
Drawings
Fig. 1 is a schematic view of a space arrangement of a steady-state ion flow field measuring device and a thruster of a plasma thruster according to an embodiment of the present invention;
fig. 2 is a schematic partial cross-sectional view of a steady-state ion flow field measuring device of a plasma thruster according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a data processing method of the apparatus of the present invention.
Detailed Description
The following detailed description of embodiments of the invention will be made with reference to the accompanying drawings.
Referring to fig. 1 and 2, an embodiment of the present invention provides a plasma thruster steady-state ion flow field measuring apparatus, including a measuring module, a power supply module, and a probe assembly, where the probe assembly includes a probe, a probe holder 1, and a motorized turntable 2, as shown in fig. 2, the probe includes an insulating housing, an ion receiving electrode 12, an incident grid 8, and an exit grid 10, one end of the insulating housing is open, the incident grid 8 is located at the opening of the insulating housing, the exit grid 10 is located in the middle of an inner cavity of the insulating housing and divides the inner cavity into two sections, the ion receiving electrode 12 is located in a section of the inner cavity of the insulating housing away from the incident grid 8, an incident hole of the incident grid 8 and an exit hole of the exit grid 10 are located on an axis of the inner cavity of the insulating housing, and the ion receiving electrode 12, the incident grid 8, and the exit grid 10 are insulated from each other, the insulation shell is fixed on the probe support 1, the electric rotary table 2 is used for driving the probe support 1 to rotate around an incident hole of the incident grid 8, the power supply module is used for providing negative bias voltage for the emergent grid 10 to filter electrons, and the measuring module is used for measuring an ion current signal of the ion receiving electrode 12 and a corner signal of the electric rotary table 2.
Specifically, when the plasma thruster steady-state ion flow field measuring device provided by the embodiment of the invention is used for measuring, the probe is placed at a measuring point O in a plume field, a power supply module provides negative bias voltage for the exit grid to filter electrons, the electric turntable is controlled to rotate around a point to be measured, meanwhile, an ion current signal of the ion receiving electrode and a corner signal of the electric turntable are measured through the measuring module, the current signal collected by the probe is a component of the ion current of the measuring point O in the axial direction of the probe, and the signal intensity of the current signal changes along with the rotation angle, so that a steady-state ion current density distribution function at the measuring point is obtained; when the rotation angle is equal to the velocity vector angle, the ion flow direction coincides with the straight line where the small holes of the incident grid and the exit grid are located, the ion current intensity reaches the maximum value, a schematic diagram of the change of the ion current density distribution function along with the rotation angle is given in fig. 3, and the vector angle of the ion velocity at the measuring point can be determined according to the size of the ion current signals at different angles.
According to the steady-state ion flow field measuring device of the plasma thruster, provided by the embodiment of the invention, the small holes of the incident grid and the emergent grid are coaxially arranged, so that an ion current signal of the ion receiving electrode has selectivity in the ion velocity direction, the probe rotates around the measuring point to obtain an ion current density distribution function in each azimuth angle at the measuring point, and simultaneously obtain a vector angle of the ion velocity; by changing the position of the measuring point of the probe in the plume region, the steady-state ion current density distribution function and the ion velocity vector angle distribution of each point in the whole plume region can be finally obtained. The device can solve the problem that the Faraday probe is insufficient in measurement in the complex plume structure of the plasma thruster, and provides an effective measurement method for researching the steady-state plume structure of the thruster in different modes.
In an alternative embodiment, the distance between the entrance hole and the exit hole is 2-3 cm, and the distance between the exit hole and the receiving surface of the ion receiving electrode 12 is 2-4 mm. When the distance between the incident hole and the exit hole is 2-3 cm, the high angular resolution of the flow field measuring device can be ensured, and when the distance between the exit hole and the ion receiving electrode is 2-4 mm, the high ion receiving efficiency of the ion receiving electrode can be ensured.
In an optional embodiment, the ion receiving electrode 12 is insulated from the exit grid 10 by an insulating mounting assembly, the ion receiving electrode 12 is a stepped structure with a T-shaped cross section, a large end surface is a receiving surface, the insulating mounting assembly includes an insulating ceramic base 11 and an inner nut 13, an inner cavity of the insulating ceramic base 11 is a stepped structure adapted to the ion receiving electrode 12, the length of a large diameter section of the inner cavity is greater than that of the large diameter section of the ion receiving electrode 12, the ion receiving electrode 12 is located in an inner cavity of the insulating ceramic base 11, the exit grid 10 is located on an end surface of the large diameter end of the inner cavity of the insulating ceramic base 11, a small diameter end of the inner cavity of the insulating ceramic base is provided with an inner nut mounting groove, and the inner nut 13 is located in the inner nut mounting groove and is in threaded connection with the diameter section of the ion receiving electrode 12. The length of the diameter section of the insulating ceramic seat is designed to be larger than the length of the large-diameter section of the ion receiving electrode, and the insulating ceramic seat and the ion receiving electrode are fixed through the inner nut, so that a certain distance is reserved between the emergent grid positioned on the end face of the large end of the insulating ceramic seat and the ion receiving electrode, and the insulating between the emergent grid and the ion receiving electrode is realized; the structure has simple assembly, convenient assembly and reliable insulation.
Further, the outer edge of the end face of the ion receiving electrode 12 with the large diameter is provided with a ring of annular protrusions. The structure can enable the ion receiving electrode to receive the scattered ion current signal, thereby improving the collection efficiency of the ion receiving electrode and being beneficial to improving the signal-to-noise ratio of the measuring device.
In an optional embodiment, the probe holder 1 includes a probe mounting hole, the probe mounting hole is a step hole, the insulating housing includes a first housing 14 and a second housing 9 that are butted, the first housing 14 is connected to the small diameter section of the probe mounting hole, the second housing 9 is installed in the large diameter section of the probe mounting hole, the inner cavity of the second housing 9 is of a step structure, the small end of the ion receiving electrode 12 is located in the first housing 14, the large end is located in the large diameter section of the inner cavity of the second housing 9, the exit grating 10 is located on the step surface of the inner cavity of the second housing 9, and the entrance grating 8 is fixed at the opening of the small diameter section of the inner cavity of the second housing 9. The beneficial effect of the above-mentioned insulating housing integrated configuration is that, can guarantee the axiality and the relative distance of fixed incident grid 8, emergent grid 10 and ion receiving electrode 12 three. In addition, the sleeving structure can greatly reduce the dark current between the electrodes, reduce the signal crosstalk and ensure the measurement precision of the measuring device.
In an optional embodiment, the first housing 14 is a hollow cylindrical structure with an open end, the open end of the first housing is provided with a flanging, the first housing 14 is inserted into the small end of the probe mounting hole, the flanging is located on the step surface of the probe mounting hole, two ends of the second housing 9 are open, the large diameter end of the inner cavity of the second housing 9 is in butt joint with the flanging of the first housing 14, the insulating ceramic seat 11 is of a stepped cylindrical structure, the small end of the insulating ceramic seat is located in the inner cavity of the first housing 14, the large end of the insulating ceramic seat is located in the large diameter section of the inner cavity of the second housing 9, and the step surface of the outside of the insulating ceramic seat 11 is attached to the flanging of the first housing 14. When the structure is assembled, the small end of the ion receiving electrode 12 assembled with the insulating installation component is pushed into the first shell 14, the outer step surface of the insulating shell is attached to the outer flanging of the first shell 14, then the assembled components are installed into the probe installation hole together, then the emergent grid 10 is pushed into the second shell 9 to be clamped at the step surface of the inner cavity of the second shell 9, the second shell 9 assembled with the emergent grid 10 is pushed into the probe installation hole to be butted with the first shell 14, and at the moment, the emergent grid 10 is clamped between the large end surface of the insulating ceramic base and the step surface of the inner cavity of the second shell 9. The structure is convenient to assemble, is beneficial to ensuring the coaxiality, and improves the assembly precision, thereby improving the reliability of the test.
Specifically, the second housing 9 is of a stepped columnar structure, a gap is formed between the second housing and the large-diameter section of the probe mounting hole, the second housing 9 is fixedly connected with the probe mounting hole through a front end top cover 6, the inner cavity of the front end top cover 6 is of a stepped structure matched with the outer surface of the second housing 9, the front end top cover 6 is in threaded connection with the probe mounting hole, an inward flange is arranged at an opening of the small-diameter section of the inner cavity of the front end top cover 6, the incident grid 8 is clamped in the inward flange, and an insulating ceramic ring 7 is padded at the contact position of the incident grid 8 and the inward flange. By adopting the structure, parts in the probe mounting hole can be gradually pressed in the process of screwing the threads of the front end top cover, and the small-diameter section of the probe mounting hole can be stressed by a gap reserved between the second shell and the large-diameter section of the probe mounting hole, so that the distance between the incident hole and the emergent hole is determined, and the angular resolution of the measuring device is ensured not to be changed.
As shown in fig. 2, the power supply module includes a bias power supply 15 and a bias power supply line 16, one end of the bias power supply line 16 is connected to the exit grating 10, the other end is connected to the negative electrode of the bias power supply 15, and the positive electrode of the bias power supply 15 is grounded. The connection mode can enable the exit hole to be in a negative voltage bias state, can effectively filter the electron current, ensures that the ion receiving electrode only receives an ion current signal, and improves the signal-to-noise ratio of the device.
As shown in fig. 2, in an alternative embodiment, the measurement module includes a signal line 17, a power connection line, and a signal acquisition circuit 18, where one end of the signal line 17 is connected to the ion receiving electrode 12, the other end is connected to an input end of the signal acquisition circuit 18, and the signal acquisition circuit 18 is connected to a negative electrode of the bias power supply 15 through the power connection line. The circuit connection mode can enable the ion receiving electrode and the emitting grid to be in a negative bias state at the same time, ensures that the ion current emitted by the ion grid is received by the signal electrode, and improves the signal-to-noise ratio of the device.
Further, as shown in fig. 1, the plasma thruster steady-state ion flow field measuring device further includes a two-dimensional moving platform, the two-dimensional moving platform includes a Z-axis telescopic rod 3, an X-direction slide rail 4 and a probe fixing base 5, the X-direction slide rail 4 is fixed on the Z-axis telescopic rod through the electric turntable 2, the Z-axis telescopic rod 3 slides along the X-direction slide rail 4 under the action of external force, and the Z-axis telescopic rod 3 is telescopic in length in the Z direction. By arranging the two-dimensional platform, the current density and the ion velocity vector information of the ion steady-state flow field at different positions in the flow field can be measured.
The embodiment of the invention also provides a steady-state ion flow field measurement method, which comprises the following steps:
the power module in the embodiment of the device provides negative bias voltage for the emergent grid 10 in the probe assembly to filter electrons;
receiving the ion current of an ion flow field measuring point through an ion receiving electrode 12 in the probe assembly, wherein the electric turntable 2 drives the probe support 1 to rotate around an incident hole of the incident grid 8 for a preset angle from a preset starting point during receiving;
meanwhile, measuring an ion current signal of the ion receiving electrode 12 and a rotation angle signal of the electric turntable 2 through a measuring module in the probe assembly, thereby determining a functional relation between current intensity and a rotation angle;
and determining the rotation angle corresponding to the maximum value of the ion current intensity according to the functional relation between the current intensity and the rotation angle to obtain the ion velocity vector angle at the measuring point.
For the description and effects of the device, reference is made to the above device embodiments, and further description is omitted here.
Further, the steady-state ion flow field measurement method further includes:
and determining the ion current density at the measuring point according to the current intensity and the diameter of the incident hole of the incident grid 8.
The following is a specific embodiment of the present invention:
as shown in fig. 1 and 2, the present embodiment provides a measurement apparatus capable of obtaining current density and ion velocity vector information of an ion steady-state flow field in a plume field, including a probe holder 1, an electric turntable 2, a z-axis telescopic rod 3, an X-direction slide rail 4, a probe fixing base 5, a front end top cover 6, an insulating ceramic ring 7, an incident grid 8, a second housing 9, an exit grid 10, an insulating ceramic seat 11, an ion receiving electrode 12, an internal nut 13, a first housing 14, a bias power supply 15, a bias power supply line 16, a signal line 17, and a signal acquisition circuit 18.
An X-direction sliding rail 4 and a z-axis telescopic rod 3 are sequentially arranged on the probe fixing seat 5, an electric turntable 2 is fixed at the tail end of the z-axis telescopic rod 3, and a probe support 1 is arranged on the electric turntable 2. The X-direction slide rail 4 and the z-axis telescopic rod 3 are adjusted to ensure the horizontal movement of the probe in the plume region. Secondly, the height of the thruster support is adjusted to ensure that the axis of the thruster is positioned in the moving plane of the probe, as shown in fig. 1.
The end stud of the ion receiving electrode 12 passes through the nut mounting hole of the insulating ceramic base 11, and after a gasket is loaded on the rear part of the ion receiving electrode, one end of the signal wire 17 is clamped and screwed by the inner nut 13. The other end of the signal wire 17 passes through a slot hole reserved in the first housing 14 and is tightened. One end of the bias power line 16 is connected to the exit grid 10, and the other end passes through the insulating ceramic base 11 and the coaxial wire hole of the first housing 14 in sequence. The signal line 17 and the bias power line 16 are led out of the vacuum chamber along a prepared hole of the probe holder 1. The first housing 14, the inner nut 13, the insulating ceramic base 11, and the ion receiving electrode 12 are integrally installed in the probe mounting hole of the probe holder 1. And (3) sequentially installing an emergent grid 10, a second shell 9, an incident grid 8 and an insulating ceramic ring 7, and finally screwing the front end top cover 6 into the probe support 1 to be screwed tightly so as to keep all the internal parts in a compressed state. Outside the vacuum chamber, a bias power line 16 is connected with the negative electrode of a bias power supply 15, a signal line 17 is connected with the negative electrode of the bias power supply 15 after passing through a signal acquisition circuit 18, and the positive electrode of the bias power supply 15 is connected with the ground wire of the vacuum chamber.
In the testing process of the ion flow field, the probe bracket 1 is vertically arranged in the plume region of the plasma thruster, and the center O of the exit hole of the probe entrance grid 8 is the position of a measuring point. Setting the bias power supply 15 to a voltage of Ub(usually U)bAbout 50V). The ion receiving electrode 12 and the exit grid 10 are connected with the negative electrode of the bias power supply, and the negative bias state of the two can filter the interference effect of electronic signals, so that the probe is ensured to only receive the ion current at the measuring point. The measuring point O of the probe is positioned on the rotating axis of the probe bracket 1, and the rotation of the electric turntable 2 can drive the whole probe to rotate around the point O. At this time, the current signal collected by the probe is a component of the ion current at the point O of the measurement point in the axial direction of the probe, and the signal intensity changes with the rotation angle, so that a steady-state ion current density distribution function at the measurement point is obtained. When the rotation angle is equal to the velocity vector angle, the ion flow direction coincides with the straight line where the small holes of the entrance grid 8 and the exit grid 10 are located, the ion current intensity reaches the maximum value, and fig. 3 shows the schematic diagram of the change of the ion current density distribution function along with the rotation angle. According to the probe rotation angle theta corresponding to the maximum value of the ion current intensityvThe vector angle of the ion velocity at the measurement point can be determined. By adjustingThe X-direction slide rail 4 and the z-axis telescopic rod 3 can change the measuring position of the probe, and finally the steady-state ion current density distribution function and the ion velocity vector angle distribution of each point in the whole plume field can be obtained.
The above description is only one embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
The invention has not been described in detail in part of the common general knowledge of those skilled in the art.
Claims (12)
1. The plasma thruster steady-state ion flow field measuring device is characterized by comprising a measuring module, a power supply module and a probe assembly, wherein the probe assembly comprises a probe, a probe support and an electric turntable, the probe comprises an insulating shell, an ion receiving electrode, an incident grid and an emergent grid, one end of the insulating shell is opened, the incident grid is positioned at the opening of the insulating shell, the emergent grid is positioned in the middle of an inner cavity of the insulating shell and divides the inner cavity into two sections, the ion receiving electrode is positioned in one section, far away from the incident grid, of the inner cavity of the insulating shell, an incident hole of the incident grid and an emergent hole of the emergent grid are positioned on the axis of the inner cavity of the insulating shell, the ion receiving electrode, the incident grid and the emergent grid are insulated from each other, the insulating shell is fixed on the probe support, and the electric turntable is used for driving the probe support to surround the incident hole of the incident grid, and the incident grid is perpendicular to the The rotating shaft with the diameter is rotated, the power supply module is used for providing negative bias voltage for the emergent grid to filter electrons, and the measuring module is used for measuring an ion current signal of the ion receiving electrode and a corner signal of the electric turntable.
2. The device for measuring the steady-state ion flow field of the plasma thruster according to claim 1, wherein the distance between the entrance hole and the exit hole is 2-3 cm, and the distance between the exit hole and the receiving surface of the ion receiving electrode is 2-4 mm.
3. The plasma thruster steady-state ion flow field measuring device according to claim 1, wherein the ion receiving electrode is insulated from the exit grid by an insulating mounting assembly, the ion receiving electrode is a stepped structure with a T-shaped cross section, the insulating mounting assembly comprises an insulating ceramic base and an inner nut, an inner cavity of the insulating ceramic base is a stepped structure matched with the ion receiving electrode, the length of a large diameter section of the inner cavity is greater than that of a large diameter section of the ion receiving electrode, the ion receiving electrode is positioned in the inner cavity of the insulating ceramic base, the exit grid is positioned at the end face of the large diameter end of the inner cavity of the insulating ceramic base, an inner nut mounting groove is formed in a small diameter section of the inner cavity of the insulating ceramic base, and the inner nut is positioned in the inner nut mounting groove and is in threaded connection with the diameter section of the ion receiving electrode.
4. The plasma thruster steady-state ion flow field measuring device as claimed in claim 3, wherein the outer edge of the end surface of the ion receiving maximum diameter end is provided with a ring of annular protrusions.
5. The plasma thruster steady-state ion flow field measuring device according to claim 3, wherein the probe holder comprises a probe mounting hole, the probe mounting hole is a stepped hole, the insulating housing comprises a first housing and a second housing which are butted with each other, the first housing is clamped to a small-diameter section of the probe mounting hole, the second housing is mounted to a large-diameter section of the probe mounting hole, an inner cavity of the second housing is of a stepped structure, a small ion receiving end is located in the first housing, a large ion receiving end is located in a large-diameter section of the inner cavity of the second housing, the exit grating is located on a stepped surface of the inner cavity of the second housing, and the entrance grating is fixed to an opening of the small-diameter section of the inner cavity of the second housing.
6. The plasma thruster steady-state ion flow field measuring device according to claim 5, wherein the first housing is a hollow cylindrical structure with an open end and an outward flange is arranged at the open end, the first housing is inserted into the small end of the probe mounting hole, the outward flange is located on the step surface of the probe mounting hole, the two ends of the second housing are open, the large diameter end of the inner cavity of the second housing is in butt joint with the outward flange of the first housing, the insulating ceramic seat is a stepped cylindrical structure, the small end is located in the inner cavity of the first housing, the large end is located in the large diameter section of the inner cavity of the second housing, and the external step surface of the insulating ceramic seat is attached to the outward flange of the first housing.
7. The plasma thruster steady-state ion flow field measuring device of claim 6, wherein the second housing has a step-shaped structure and a gap is formed between the second housing and the large-diameter section of the probe mounting hole, the second housing is fixedly connected with the probe mounting hole through a front end top cover, an inner cavity of the front end top cover has a step structure matched with the outer surface of the second housing, the front end top cover is in threaded connection with the probe mounting hole, an inner flange is arranged at an opening of the small-diameter section of the inner cavity of the front end top cover, the incident grid is clamped in the inner flange, and an insulating ceramic ring is padded at a contact position of the incident grid and the inner flange.
8. The plasma thruster steady-state ion flow field measuring device of claim 7, wherein the power supply module comprises a bias power supply and a bias power supply line, one end of the bias power supply line is connected with the exit grid, the other end of the bias power supply line is connected with the negative pole of the bias power supply, and the positive pole of the bias power supply is grounded.
9. The plasma thruster steady-state ion flow field measuring device according to claim 8, wherein the measuring module comprises a signal line, a power supply connecting line and a signal collecting circuit, one end of the signal line is connected with the ion receiving electrode, the other end of the signal line is connected with an input end of the signal collecting circuit, and the signal collecting circuit is connected with a negative electrode of the bias power supply through the power supply connecting line.
10. The plasma thruster steady-state ion flow field measuring device of claim 1, further comprising a two-dimensional moving platform, wherein the two-dimensional moving platform comprises a z-axis telescopic rod and an X-direction slide rail, the probe support is fixed on the z-axis telescopic rod through the electric turntable, and the z-axis telescopic rod slides along the X-direction slide rail under the action of external force.
11. A method of steady state ion flow field measurement, comprising:
providing a negative bias voltage to an exit grid in a probe assembly to filter electrons through a power module in the apparatus provided in any one of claims 1 to 10;
receiving the ion current of an ion flow field measuring point through an ion receiving electrode in the probe assembly, and driving the probe support to rotate around an incident hole of the incident grid for a preset angle from a preset starting point by the electric turntable during receiving;
meanwhile, measuring an ion current signal of the ion receiving electrode and a corner signal of the electric turntable through a measuring module in the probe assembly so as to determine a functional relation between current intensity and a rotation angle;
and determining the rotation angle corresponding to the maximum value of the ion current intensity according to the functional relation between the current intensity and the rotation angle to obtain the ion velocity vector angle at the measuring point.
12. A steady state ion flow field measurement method as recited in claim 11, further comprising:
and determining the ion current density at the measuring point according to the current intensity and the diameter of the incident hole of the incident grid.
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| CN111796318B (en) * | 2020-07-01 | 2022-07-12 | 合肥兆科机电科技有限公司 | Two-dimensional adjustable remote control telescopic probe structure system |
| CN112291913A (en) * | 2020-09-30 | 2021-01-29 | 兰州空间技术物理研究所 | Device and method for diagnosing plasma inside discharge chamber of ion thruster |
| CN112326253B (en) * | 2020-10-28 | 2022-08-16 | 哈尔滨工业大学 | Thrust vector eccentricity diagnostic device |
| CN112530229B (en) * | 2020-12-30 | 2022-05-31 | 哈尔滨工业大学 | Space plasma parameter diagnosis device based on four-degree-of-freedom motion mechanism |
| CN113466920A (en) * | 2021-07-02 | 2021-10-01 | 兰州空间技术物理研究所 | Electric propulsion beam characteristic parameter diagnosis equipment |
| CN114323658A (en) * | 2022-01-05 | 2022-04-12 | 哈尔滨工业大学 | Plasma propulsion plume diagnosis probe |
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| US3699331A (en) * | 1971-08-27 | 1972-10-17 | Paul W Palmberg | Double pass coaxial cylinder analyzer with retarding spherical grids |
| CN1156868C (en) * | 1999-11-19 | 2004-07-07 | 东京电子株式会社 | Stabilized oscillator circuit for plasma density measurement |
| CN101366095B (en) * | 2005-12-02 | 2010-11-10 | 阿利斯公司 | Ion sources, systems and methods |
| CN104183447B (en) * | 2013-05-27 | 2018-05-22 | 斯伊恩股份有限公司 | High energy ion injection device |
| CN105022083B (en) * | 2015-07-13 | 2016-10-12 | 兰州空间技术物理研究所 | A kind of ion-conductance advances line double charge ions test device and assembly method thereof |
| CN107741599A (en) * | 2017-09-01 | 2018-02-27 | 兰州空间技术物理研究所 | A kind of thruster ion beam current center line laser locating apparatus and method |
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