CN117572136A - Detection system suitable for measuring response time of electric thruster - Google Patents
Detection system suitable for measuring response time of electric thruster Download PDFInfo
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- CN117572136A CN117572136A CN202410056847.5A CN202410056847A CN117572136A CN 117572136 A CN117572136 A CN 117572136A CN 202410056847 A CN202410056847 A CN 202410056847A CN 117572136 A CN117572136 A CN 117572136A
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- thruster
- slide bar
- fixedly connected
- response time
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- 230000004044 response Effects 0.000 title claims abstract description 34
- 238000001514 detection method Methods 0.000 title claims description 27
- 239000000523 sample Substances 0.000 claims abstract description 62
- 238000005259 measurement Methods 0.000 claims abstract description 24
- 238000005070 sampling Methods 0.000 claims description 10
- 238000007599 discharging Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 6
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 3
- 229910052750 molybdenum Inorganic materials 0.000 claims description 3
- 239000011733 molybdenum Substances 0.000 claims description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical group [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 3
- 229910052721 tungsten Inorganic materials 0.000 claims description 3
- 239000010937 tungsten Substances 0.000 claims description 3
- 238000010884 ion-beam technique Methods 0.000 abstract description 7
- 230000015572 biosynthetic process Effects 0.000 abstract description 2
- 238000004088 simulation Methods 0.000 abstract description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Plasma Technology (AREA)
Abstract
The utility model relates to a detecting system suitable for electric thruster response time measurement, through vacuum environment simulator simulation vacuum environment, the ion beam current that electric thruster produced is collected to faraday probe behind the electric thruster work, and collect discharge current signal and ion current signal through oscilloscope and high accuracy ampere meter, faraday probe can remove on vertical slide bar and horizontal slide bar, with horizontal distance and vertical height between regulation faraday probe and the electric thruster, drive the swinging boom through the gyrator and rotate, thereby drive faraday probe rotation, with this degree of the contained angle that adjusts faraday probe's axis and electric thruster's axis formation, thereby improve faraday probe's collection efficiency, make measuring result more accurate.
Description
Technical Field
The application relates to the technical field of measurement, in particular to a detection system suitable for measuring response time of an electric thruster.
Background
Space science refers to science of physical, astronomical, chemical, life and other natural phenomena and rules thereof which take place in the space between the sun and the earth, the space between the planets and the whole space by utilizing spacecraft research space (space is an objective existence form of a substance relative to time and is expressed by length, width, height and size). Space science is based on aerospace technology, including aspects such as space flight, space exploration, and space development. It can not only reveal the mystery of universe, but also bring great benefit to human beings.
The satellite platform is more utilized in space science, and the performance parameter index of the micro propulsion system of the satellite platform is higher, and the response time of the propulsion system is one of the key indexes. The response time of the thruster mainly comprises two types, one is the time taken for starting the thruster to output the rated thrust, and the other is the time required for the change of the thrust when the thruster is shifted from one working condition to the other working condition.
The electric thruster belongs to one of the thrusters, and the response time of the electric thruster is mainly related to two factors: the application time of the power supply and the set-up time of the plasma, in which case the response time of the electric thruster is only dependent on the set-up time of the plasma. While the establishment of the plasma is generally faster, the response time of the thruster is generally on the order of several ms to ten ms in the case of a more stable plasma generation. However, the current measuring device for the response time of the electric thruster generally has difficulty in accurately measuring the response time of the electric thruster, and the collection efficiency of the ion beam current generated by the electric thruster during measurement is low, so that the measurement efficiency is low.
Disclosure of Invention
Based on this, the present application is generally difficult to accurately measure the response time of an electric thruster for a current measurement device of the response time of the electric thruster, and the collection efficiency of the ion beam current generated by the electric thruster during measurement is low, which results in the technical problem of low measurement efficiency, and provides a detection system suitable for the measurement of the response time of the electric thruster, where the detection system suitable for the measurement of the response time of the electric thruster includes:
a vacuum environment simulator for providing a vacuum environment;
the electric thruster is fixedly connected to one end of the thruster mounting seat, the lower end of the thruster mounting seat is fixedly connected to the fixed support, and the Faraday probe is fixedly connected to one end of the probe mounting seat;
the detection assembly comprises a thruster discharging circuit, an oscilloscope, an ion current collecting circuit and a high-precision ammeter, wherein one end of the thruster discharging circuit is electrically connected with the electric thruster, the oscilloscope is connected with the thruster discharging circuit in series, the ion current collecting circuit is electrically connected with the Faraday probe, and the high-precision ammeter is electrically connected with the ion current collecting circuit.
The utility model relates to a detecting system suitable for electric thruster response time measurement, through vacuum environment simulator simulation vacuum environment, the ion beam current that electric thruster produced is collected to faraday probe behind the electric thruster work, and collect discharge current signal and ion current signal through oscilloscope and high accuracy ampere meter, faraday probe can remove on vertical slide bar and horizontal slide bar, with horizontal distance and vertical height between regulation faraday probe and the electric thruster, drive the swinging boom through the gyrator and rotate, thereby drive faraday probe rotation, with this degree of the contained angle that adjusts faraday probe's axis and electric thruster's axis formation, thereby improve faraday probe's collection efficiency, make measuring result more accurate.
Drawings
Fig. 1 is a schematic structural diagram of a detection system suitable for measuring response time of an electric thruster according to an embodiment of the present application.
Fig. 2 is a schematic perspective view of a position adjustment assembly and an angle adjustment assembly for an operation method for measuring response time of an electric thruster according to an embodiment of the present application.
Fig. 3 is a circuit diagram of a detection system suitable for measuring response time of an electric thruster according to an embodiment of the present invention.
Reference numerals:
1. an electric thruster; 2. a thruster mount; 3. a fixed bracket; 3a, mounting holes;
4. a Faraday probe; 4a, a collector; 4b, shielding the shell; 4c, a bias voltage source;
5. a probe mounting seat; 6. a rotary motor; 7. a rotating arm; 8. a horizontal slide bar; 8a, a horizontal spring;
9. a vertical slide bar; 9a, vertical springs; 10. a vacuum environment simulator; 11. a thruster discharge circuit;
12. a discharge loop sampling resistor; 13. an oscilloscope; 14. an ion current collection circuit;
15. an ion current loop sampling resistor; 16. a high-precision ammeter; 17. a thruster assembly;
18. a detection assembly; 19. a position adjustment assembly; 20. and an angle adjusting component.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application will be further described in detail with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the present application.
The application provides a detection system suitable for use in response time measurement of an electric thruster. It should be noted that the detection system suitable for measuring response time of an electric thruster provided by the present application is applicable to any kind of electric thruster.
As shown in fig. 1, the present application provides a detection system suitable for use in electric thruster response time measurement, comprising a vacuum environment simulator 10, a thruster assembly 17 and a detection assembly 18.
The vacuum environment simulator 10 is used to provide a vacuum environment. The thruster assembly 17 comprises an electric thruster 1, a thruster mount 2, a fixed bracket 3, a Faraday probe 4 and a probe mount 5, wherein the electric thruster 1 is fixedly connected with one end of the thruster mount 2, the lower end of the thruster mount 2 is fixedly connected with the fixed bracket 3, and the Faraday probe 4 is fixedly connected with one end of the probe mount 5. The detection assembly 18 comprises a thruster discharging circuit 11, an oscilloscope 13, an ion current collecting circuit 14 and a high-precision ammeter 16, one end of the thruster discharging circuit 11 is electrically connected with the electric thruster 1, the oscilloscope 13 is connected with the thruster discharging circuit 11 in series, the ion current collecting circuit 14 is electrically connected with the Faraday probe 4, and the high-precision ammeter 16 is electrically connected with the ion current collecting circuit 14.
Specifically, the vacuum environment simulator 10 may generate a vacuum ofVacuum environment of Pa.
The electric thruster 1 may be a hall thruster, an ion thruster, a field emission thruster, an arc thruster, a laser plasma thruster or other kind of electric thruster 1 capable of generating plasma. When the electric thruster 1 is a hall thruster, an electron source is required to provide electrons required for generating plasma for the hall thruster, and a high voltage power supply is also required to provide discharge high voltage for the hall thruster.
In this embodiment, the vacuum environment simulator 10 simulates a vacuum environment, the faraday probe 4 collects the ion beam current generated by the electric thruster 1 after the electric thruster 1 works, and the oscilloscope 13 and the high-precision ammeter 16 collect the discharge current signal and the ion current signal, the faraday probe 4 can move on the vertical sliding rod 9 and the horizontal sliding rod 8 to adjust the horizontal distance and the vertical height between the faraday probe 4 and the electric thruster 1, and the rotating arm 7 is driven to rotate by the rotary motor 6, so as to drive the faraday probe 4 to rotate, thereby adjusting the degree of the included angle formed by the central axis of the faraday probe 4 and the central axis of the electric thruster 1, and further improving the collection efficiency of the faraday probe 4, and making the measurement result more accurate.
As shown in fig. 2, in an embodiment of the present application, the detection system for measuring response time of an electric thruster further includes a position adjustment assembly 19, where the position adjustment assembly 19 includes a vertical slide bar 9 and a horizontal slide bar 8, one end of the probe mount 2 is fixedly connected to one end of the vertical slide bar 9, the other end of the vertical slide bar 9 is fixedly connected to the horizontal slide bar 8, and the horizontal slide bar 8 is fixedly connected to the inside of the vacuum environment simulator 10.
Specifically, the horizontal distance between the faraday probe 4 and the hall thruster is generally between 15cm and 100cm, and is determined according to the ion energy and the ion density of the thruster, and the more the ion energy is, the higher the ion density is, the more the horizontal distance between the faraday probe and the hall thruster is.
In this embodiment, the probe mount 2 moves up and down along the vertical slide bar 9 to adjust the height of the faraday probe 4, so that the vertical height of the faraday probe 4 is consistent with the height of the hall thruster, and the vertical slide bar 9 moves horizontally on the horizontal slide bar 8 to adjust the horizontal distance between the faraday probe 4 and the hall thruster.
In one embodiment of the present application, as shown in fig. 1, the horizontal slide bar 8 and the vertical slide bar 9 are perpendicular to each other, and when the vacuum environment simulator 10 is placed horizontally, the straight line where the horizontal slide bar 8 is located coincides with the horizontal line.
Specifically, in this embodiment, the horizontal distance between the faraday probe 4 and the hall thruster may be 15cm, 20cm, or 30cm.
In this embodiment, the horizontal sliding rod 8 is set to be in a horizontal state, so as to ensure that the center of the electric thruster 1 and the collector 4a of the faraday probe 4 can be at the same height, so as to improve the collection efficiency of the faraday probe 4 and ensure the accuracy of measurement.
As shown in fig. 2, in an embodiment of the present application, one end of the vertical sliding rod 9 is fixedly connected with a vertical spring 9a, one end of the probe mounting seat 5 is fixedly connected with the vertical spring 9a, one end of the horizontal sliding rod 8 is fixedly connected with a horizontal spring 8a, and one end of the vertical sliding rod 9 is fixedly connected with the horizontal spring 8a.
In this embodiment, the vertical spring 9a may cooperatively adjust the vertical height of the probe mount 5 to drive the faraday probe 4 to move, thereby adjusting the height of the faraday probe 4, so that the height of the faraday probe 4 is the same as the height of the electric thruster 1, and after the height adjustment of the faraday probe 4 is completed, the horizontal spring 8a may adjust the horizontal position of the vertical slide bar 9 to drive the faraday probe 4 to move, thereby adjusting the horizontal distance between the faraday probe 4 and the electric thruster 1.
As shown in fig. 2, in an embodiment of the present application, the detection system for measuring response time of an electric thruster further includes an angle adjustment assembly 20, where the angle adjustment assembly 20 includes a rotating arm 7 and a rotary motor 6, one end of the rotating arm 7 is fixedly connected to the horizontal sliding rod 8, the other end of the rotating arm 7 is fixedly connected to the rotary motor 6, and the rotary motor 6 is fixedly connected to the bottom surface of the vacuum environment simulator 10.
Specifically, the angle formed by the central axis of the faraday probe 4 and the central axis of the electric thruster 1 in this embodiment may be 0 ° or 30 °.
In this embodiment, after the adjustment of the horizontal position and the vertical position of the faraday probe 4 is completed, the rotary motor 6 works to drive the rotary arm 7 to rotate, so as to drive the horizontal sliding rod 8 at one end of the rotary arm 7 to rotate, thereby adjusting the inclination angle of the faraday probe 4, and adjusting the size of the included angle formed by the central axis of the faraday probe 4 and the central axis of the electric thruster 1, so that the collection efficiency of the faraday probe 4 is higher.
As shown in fig. 2, in an embodiment of the present application, the height of the thruster mount 2 is the same as the height of the probe mount 5, a mounting hole 3a is formed at one end of the fixing bracket 3, and the thruster mount 5 is fixedly connected to the fixing bracket 3 through the mounting hole 3 a.
Specifically, the number of the mounting holes 3a is plural, and the plural groups of the mounting holes 3a are arranged on the fixing bracket 3 at equal intervals.
In this embodiment, the thruster mount 2 is fixedly connected with the fixed support 3 through the mounting holes 3a, and the mounting positions of the thruster mount 5 are convenient to adjust due to the multiple groups of mounting holes 3a, so that the height of the electric thruster 1 and the height of the faraday probe 4 are more easily unified.
As shown in fig. 1, in an embodiment of the present application, the vacuum environment simulator 10 is hollow, and a closing plate is rotatably connected to one end of the vacuum environment simulator 10.
Specifically, the thruster assembly 17, the position adjustment assembly 19 and the angle adjustment assembly 20 are all located inside the vacuum environment simulator 10.
In this embodiment, the closing plate is adjusted to control the opening and closing of the vacuum environment simulator 10, and when the closing plate is closed, the vacuum environment can be simulated inside the vacuum environment simulator 10, so as to provide a high vacuum environment for the ignition test of the electric thruster 1.
As shown in fig. 1, in an embodiment of the present application, a discharge loop sampling resistor 12 is connected in series to the thruster discharge circuit 11, and an ion current loop sampling resistor 15 is connected in series to the ion current acquisition loop 14.
Specifically, when the current to be collected is large, the discharge loop sampling resistor 12 with a small resistance value can be selected. When measuring a watt-level thruster, the current is about microampere or milliamp, so that the discharge loop sampling resistor 12 with larger resistance is required to amplify the current.
In this embodiment, the resistance value of the discharge loop sampling resistor 12 may be 3000 Ω or 10000 Ω. The ion current loop sampling resistor 15 protects the ion current acquisition loop 14.
As shown in fig. 3, in an embodiment of the present application, the faraday probe 4 comprises a collector 4a, a shielding enclosure 4b, and a bias voltage source 4c.
In this embodiment, the collector 4a collects the ion beam current generated by the electric thruster 1, and the bias voltage source 4c may apply a bias voltage to the collector 4a and the shielding shell 4b, which is negatively biased with respect to the zero potential, so as to repel electrons in the ion beam current generated by the electric thruster 1.
As shown in fig. 3, in an embodiment of the present application, the surface material of the collector 4a is tungsten or molybdenum, and the bias voltage of the bias voltage source 4c may be-15V, -20V or-30V.
Specifically, the surface material of the collector 4a is a material having a low secondary electron emission coefficient.
In this embodiment, tungsten or molybdenum is selected as the surface material of the collector 4a, so that the collection efficiency of the faraday probe 4 can be effectively improved.
The technical features of the above embodiments may be combined arbitrarily, and the steps of the method are not limited to the execution sequence, so that all possible combinations of the technical features in the above embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description of the present specification.
The above examples only represent a few embodiments of the present application, which are described in more detail and are not to be construed as limiting the scope of the present application. It should be noted that it would be apparent to those skilled in the art that various modifications and improvements could be made without departing from the spirit of the present application, which would be within the scope of the present application. Accordingly, the scope of protection of the present application shall be subject to the appended claims.
Claims (10)
1. A detection system adapted for use in an electric thruster response time measurement, the detection system adapted for use in an electric thruster response time measurement comprising:
a vacuum environment simulator for providing a vacuum environment;
the electric thruster is fixedly connected to one end of the thruster mounting seat, the lower end of the thruster mounting seat is fixedly connected to the fixed support, and the Faraday probe is fixedly connected to one end of the probe mounting seat;
the detection assembly comprises a thruster discharging circuit, an oscilloscope, an ion current collecting circuit and a high-precision ammeter, wherein one end of the thruster discharging circuit is electrically connected with the electric thruster, the oscilloscope is connected with the thruster discharging circuit in series, the ion current collecting circuit is electrically connected with the Faraday probe, and the high-precision ammeter is electrically connected with the ion current collecting circuit.
2. The detection system for electric thruster response time measurement according to claim 1, further comprising a position adjustment assembly, the position adjustment assembly comprising a vertical slide bar and a horizontal slide bar, one end of the probe mount being fixedly connected to one end of the vertical slide bar, the other end of the vertical slide bar being fixedly connected to the horizontal slide bar, the horizontal slide bar being fixedly connected to the inside of the vacuum environment simulator.
3. The system of claim 2, wherein the horizontal slide bar is perpendicular to the vertical slide bar, and wherein the horizontal slide bar is aligned with a horizontal line when the vacuum environment simulator is placed horizontally.
4. The detection system for electrical thruster response time measurement according to claim 3, wherein one end of the vertical slide bar is fixedly connected with a vertical spring, one end of the probe mount is fixedly connected with a vertical spring, one end of the horizontal slide bar is fixedly connected with a horizontal spring, and one end of the vertical slide bar is fixedly connected with a horizontal spring.
5. The detection system for electric thruster response time measurement according to claim 1, further comprising an angle adjustment assembly comprising a rotating arm and a rotary motor, one end of the rotating arm being fixedly connected to the horizontal slide bar, the other end of the rotating arm being fixedly connected to the rotary motor, the rotary motor being fixedly connected to the bottom surface of the vacuum environment simulator.
6. The detection system for electrical thruster response time measurement according to claim 1, wherein the height of the thruster mount is the same as the height of the probe mount, a mounting hole is provided at one end of the fixing bracket, and the thruster mount is fixedly connected to the fixing bracket through the mounting hole.
7. The detection system for electrical thruster response time measurement according to claim 1, wherein the vacuum environment simulator is hollow inside, and a closing plate is rotatably connected to one end of the vacuum environment simulator.
8. The detection system for electrical thruster response time measurement according to claim 1, wherein a discharge loop sampling resistor is connected in series in the thruster discharge circuit, and an ion current loop sampling resistor is connected in series in the ion current collection loop.
9. The detection system for electrical thruster response time measurement of claim 1, wherein the faraday probe comprises a collector, a shielding enclosure, and a bias voltage source.
10. The detection system for electrical thruster response time measurement according to claim 9, wherein the surface material of the collector is tungsten, molybdenum or other material with low secondary electron emission coefficient, and the bias voltage of the bias voltage source can be-15V, -20V or-30V.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410056847.5A CN117572136A (en) | 2024-01-16 | 2024-01-16 | Detection system suitable for measuring response time of electric thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410056847.5A CN117572136A (en) | 2024-01-16 | 2024-01-16 | Detection system suitable for measuring response time of electric thruster |
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| CN117572136A true CN117572136A (en) | 2024-02-20 |
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| CN202410056847.5A Pending CN117572136A (en) | 2024-01-16 | 2024-01-16 | Detection system suitable for measuring response time of electric thruster |
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-
2024
- 2024-01-16 CN CN202410056847.5A patent/CN117572136A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001237234A (en) * | 2000-02-21 | 2001-08-31 | Hitachi Ltd | Plasma treatment apparatus and treatment method |
| CN101539481A (en) * | 2009-04-17 | 2009-09-23 | 北京航空航天大学 | Plume diagnosis device of electric propulsion engine |
| CN110554265A (en) * | 2019-09-11 | 2019-12-10 | 北京航空航天大学 | double-sided probe, double-sided probe diagnostic system and diagnostic method |
| CN110618444A (en) * | 2019-09-24 | 2019-12-27 | 北京航空航天大学 | Beam current measuring system and main system of electric thruster |
| CN112729641A (en) * | 2020-12-01 | 2021-04-30 | 上海空间推进研究所 | System and method for measuring response time of cold air thruster based on variable dielectric capacitance bridge |
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