CN116930668B - Detection system and operation method for measuring response time of electric thruster - Google Patents
Detection system and operation method for measuring response time of electric thruster Download PDFInfo
- Publication number
- CN116930668B CN116930668B CN202311189089.6A CN202311189089A CN116930668B CN 116930668 B CN116930668 B CN 116930668B CN 202311189089 A CN202311189089 A CN 202311189089A CN 116930668 B CN116930668 B CN 116930668B
- Authority
- CN
- China
- Prior art keywords
- electric
- signal
- thruster
- electric thruster
- response time
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000004044 response Effects 0.000 title claims abstract description 54
- 238000001514 detection method Methods 0.000 title claims abstract description 23
- 238000000034 method Methods 0.000 title claims abstract description 23
- 230000003287 optical effect Effects 0.000 claims abstract description 27
- 238000010586 diagram Methods 0.000 claims description 17
- 238000005259 measurement Methods 0.000 claims description 16
- 238000007599 discharging Methods 0.000 claims description 13
- 238000004088 simulation Methods 0.000 claims description 10
- 238000005070 sampling Methods 0.000 claims description 8
- 238000007781 pre-processing Methods 0.000 claims description 5
- 230000007935 neutral effect Effects 0.000 claims description 3
- 238000009499 grossing Methods 0.000 claims description 2
- 238000012545 processing Methods 0.000 claims description 2
- 238000004364 calculation method Methods 0.000 claims 1
- 238000010884 ion-beam technique Methods 0.000 abstract description 3
- 150000002500 ions Chemical class 0.000 description 6
- 238000000691 measurement method Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 229910052732 germanium Inorganic materials 0.000 description 1
- GNPVGFCGXDBREM-UHFFFAOYSA-N germanium atom Chemical compound [Ge] GNPVGFCGXDBREM-UHFFFAOYSA-N 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 229910052724 xenon Inorganic materials 0.000 description 1
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Plasma Technology (AREA)
Abstract
The application relates to a detection system and an operation method for measuring response time of an electric thruster, wherein the operation method for measuring response time of the electric thruster is characterized in that discharge high voltage is applied to the electric thruster, an optical signal of ion beam current generated by the electric thruster is collected through an avalanche photodiode after the electric thruster works and converted into an electric signal, the electric signal generated by the avalanche photodiode is collected through an oscilloscope, and the response time of the electric thruster is calculated through the collected electric signal and the electric signal.
Description
Technical Field
The application relates to the technical field of measurement, in particular to a detection system and an operation method for measuring response time of an electric thruster.
Background
The electric thruster is a thruster which generates weak thrust by utilizing the reaction force of ions, and can be subdivided according to different ion generation and acceleration modes, and mainly comprises a Hall thruster, an ion thruster and the like, which are basically the same, and the electric thruster ionizes inert gas xenon by electric energy to form plasma composed of ions and electrons, wherein the ions are accelerated and ejected under the action of an electric field to generate thrust.
The propulsion system of a thruster is the most important part of a thruster, and the response time of the propulsion system is a key indicator of the performance parameters of the propulsion system. The response time of the thrust system mainly comprises two types, one is the time taken for starting the thruster to output rated thrust, and the other is the time required for thrust change when the thruster is shifted from one working condition to the other working condition.
The current measurement method for the response time of the electric thruster generally pushes the weak force measurement device to generate offset through the thruster, and the response time of the thruster is measured through the time generated by the offset, but the telecommunication acquired in the acquisition process of the measurement method can generate larger deviation with the real signal, so that the measured response time is not accurate enough.
Disclosure of Invention
Based on the above, the application aims at the technical problems that the current measurement method for the response time of the electric thruster generally generates offset by pushing a weak force measurement device through the thruster and measures the response time of the thruster through the time generated by the offset, but the telecommunication acquired in the acquisition process of the measurement method can generate larger deviation from a real signal, so that the measured result of the response time is not accurate enough, and provides a detection system and an operation method for the response time measurement of the electric thruster.
In one aspect, the application provides a method of operating the electric thruster response time measurement.
The operation method of the response time measurement of the electric thruster comprises the following steps:
configuring hardware equipment, starting an avalanche photodiode, and moving the avalanche photodiode to enable the avalanche photodiode to enter a working position;
starting an electric thruster, applying discharge high voltage to the electric thruster, and collecting a discharge current signal;
collecting the optical signal by an avalanche photodiode;
and preprocessing the discharge current signal and the optical signal, and calculating the response time of the electric thruster according to the preprocessed discharge current signal and the preprocessed optical signal.
In another aspect, the present application further provides a detection system suitable for measuring response time of an electric thruster, applying the detection method suitable for measuring response time of an electric thruster mentioned in the foregoing, where the detection system for measuring response time of an electric thruster includes:
an electric thruster;
the vacuum environment simulation device is used for simulating a vacuum environment;
the adjusting assembly comprises a first sliding table extending towards the first direction, a second sliding table extending towards the second direction, a third sliding table extending towards the third direction and a coupler, wherein the first sliding table is fixedly connected with the second sliding table, the third sliding table is fixedly connected with the second sliding table, and the coupler is fixedly connected between the first sliding tables;
the driving assembly comprises a first motor, a second motor and a third motor, wherein the first motor is fixedly connected to one end of the first sliding table, the second motor is fixedly connected to one end of the second sliding table, and the third motor is fixedly connected to one end of the third sliding table;
the collecting assembly comprises an avalanche photodiode, a collecting loop, a discharging loop and an oscilloscope, wherein the avalanche photodiode is fixedly connected to the driving assembly, one end of the collecting loop is electrically connected with the avalanche photodiode, one end of the discharging loop is electrically connected with the electric thruster, and the oscilloscope is electrically connected with the collecting loop and the discharging loop.
The application relates to a detection system and an operation method for measuring response time of an electric thruster, which are used for applying discharge high voltage to the electric thruster, collecting optical signals of ion beam current generated by the electric thruster through an avalanche photodiode after the electric thruster works, converting the optical signals into electric signals, collecting the electric signals generated by the avalanche photodiode through an oscilloscope, and calculating the response time of the electric thruster through the collected electric signals and the optical signals.
Drawings
FIG. 1 is a flow chart of a method of operation for an electric thruster response time measurement in accordance with an embodiment of the present application.
Fig. 2 is a circuit diagram of an operation method suitable for measuring response time of an electric thruster according to an embodiment of the present application.
Fig. 3 is a graph of a discharge current signal and a graph of an ion current signal for an operation method for measuring response time of an electric thruster according to an embodiment of the present application.
Fig. 4 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. 5 is a schematic structural diagram of an adjusting assembly and a driving assembly of a detection system for measuring response time of an electric thruster according to an embodiment of the present application.
Fig. 6 is a perspective view of a shielding assembly of a detection system for electric thruster response time measurement in accordance with an embodiment of the present application.
Reference numerals:
1. an electric thruster; 2. a vacuum environment simulation device; 3. an adjustment assembly; 301. a first sliding table;
302. a second sliding table; 303. a third sliding table; 304. a coupling; 4. a drive assembly;
401. a first motor; 402. a second motor; 403. a third motor; 5. a collection assembly;
501. an avalanche photodiode; 502. a collection loop; 503. a discharge circuit; 504. an oscilloscope;
6. an electric thruster holder; 7. a diode holder; 8. a shielding assembly; 801. a shielding housing;
802. shielding the transparent shell; 9. a discharge loop sampling resistor; 10. the acquisition loop samples the resistor.
Detailed Description
The present application will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present application more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the application.
The application provides a detection system and an operation method for measuring response time of an electric thruster. It should be noted that the detection system and the operation method for measuring the response time of the electric thruster provided by the application are applied to any kind of electric thrusters.
As shown in fig. 1, the present application provides a detection system and an operation method for measuring response time of an electric thruster, including:
s100, configuring hardware equipment, starting an avalanche photodiode, and moving the avalanche photodiode to enable the avalanche photodiode to enter a working position;
s200, starting an electric thruster, applying discharge high voltage to the electric thruster, and collecting a discharge current signal;
s300, collecting optical signals through an avalanche photodiode;
s400, preprocessing the discharge current signal and the optical signal, and calculating the response time of the electric thruster according to the preprocessed discharge current signal and the preprocessed optical signal.
In particular, avalanche photodiodes refer to photosensitive elements used in laser communication. After reverse bias is applied to the P-N junction of a photodiode made of silicon or germanium, the incident light is absorbed by the P-N junction to form photocurrent. Increasing the reverse bias voltage causes an "avalanche" (i.e., a doubling of the photocurrent) phenomenon, and such a diode is referred to as an "avalanche photodiode".
In this embodiment, a discharge high voltage is applied to the electric thruster, the electric thruster collects an optical signal of an ion beam current generated by the electric thruster through the avalanche photodiode after working, the optical signal is converted into an electric signal, the electric signal generated by the avalanche photodiode is collected through the oscilloscope, and the response time of the electric thruster is calculated through the collected electric signal and the optical signal.
In an embodiment of the present application, the S100 includes the following S110 to S130:
s110, connecting a hardware circuit to simulate a vacuum environment;
s120, applying bias voltage to the avalanche photodiode;
and S130, adjusting the distance and the angle between the avalanche photodiode and the electric thruster.
Specifically, the light intensity is inversely proportional to the square of the distance to the light source, i.e., the light intensity can be calculated using the formula e=i/D, where E is the illuminance, I is the point source light intensity, and D is the distance. Therefore, the maximum value of the distance between the light intensity of the thruster and the light intensity of the avalanche photodiode can be calculated according to the light intensity of the thruster and the light intensity of the avalanche photodiode, and the distance between the Hall thruster and the avalanche photodiode can be selected in the interval.
In this embodiment, a hall thruster is selected as the electric thruster, and an avalanche photodiode of S16453 series is selected, and the circuit connection diagram is shown in fig. 2.
And connecting hardware circuits, and simulating a vacuum environment through a vacuum environment simulation device to enable the Hall thruster to have discharge test conditions.
Bias voltages are applied to the avalanche photodiodes, which are between 200V and 450V for the S16453 series of avalanche photodiodes.
And the Hall thruster is moved, so that the Hall thruster is driven by the first motor, the second motor and the third motor to move along the first sliding table, the second sliding table and the third sliding table respectively, the central axis of the Hall thruster is overlapped with the central axis of the avalanche photodiode, and the distance between the Hall thruster and the avalanche photodiode is 20cm.
In an embodiment of the present application, the S200 includes S210 to S230:
s210, starting an electron source of the electric thruster, and providing neutral gas;
s220, turning on a high-voltage power supply, applying the high-voltage power supply to the electric thruster, and collecting a discharge current signal of the electric thruster, and recording the discharge current signal as a first electric signal.
In this embodiment, after the electron source of the hall thruster is turned on, neutral gas required for discharging the hall thruster needs to be provided to the vacuum environment, so that the hall thruster enters a state to be ignited.
After the high-voltage power supply is started, discharging high voltage is applied to the Hall thruster, and the voltage at two ends of the sampling resistor of the discharging loop is collected through the oscilloscope so as to collect discharging current signals from the Hall thruster, and the discharging current signals are recorded as first electric signals.
In an embodiment of the present application, the S400 includes:
s410, collecting optical signals in plasma beam generated by an electric thruster through an avalanche photodiode, converting the optical signals into electric signals, collecting the converted electric signals, and recording the electric signals as second electric signals;
s420, closing the hardware equipment, and performing smoothing on the first electric signal and the second electric signal;
s430, calculating a discharge reference line L1 of a signal waveform diagram of the first electric signal, and extracting a starting moment T1;
s440, calculating a starting reference line L2 of a signal waveform diagram of the second electric signal, and extracting an ending time T2;
s450, calculating response time T according to the response time T1 and the ending time T2.
In particular, data acquired from real environments are often aliased with weak noise, including noise due to system instability, and also with ambient-induced glitches, which all need to be removed or reduced as much as possible before processing the signal.
In this embodiment, the avalanche photodiode may convert the collected optical signal into an electrical signal, so that the collected signal is closer to the real signal, and no filtering process is required during preprocessing, thereby making the measurement accuracy higher.
In an embodiment of the present application, the S430 includes:
s431, a first current average value before the thruster discharges in a signal waveform diagram of the first electric signal is calculated, a straight line parallel to the X axis is made at a point corresponding to the first current average value, and the straight line is marked as a discharge reference line L1.
As shown in fig. 3, in this embodiment, the current signals before discharge in the first electric signal of the electric thruster are summed and a first current average value is taken, a straight line parallel to the X axis of the signal waveform diagram is made at a point corresponding to the first current average value, and this straight line is denoted as a discharge reference line L1.
After the electric thruster is started, the discharge current can rise greatly. Because the discharge current signal floats up and down on the discharge reference line L1 due to the existence of the power frequency noise, the last intersection point of the signal waveform diagram of the first electric signal and the discharge reference line L1 is selected as the starting time T1 of the electric thruster, and it can be seen from fig. 3 that t1= -1.76ms.
In an embodiment of the present application, the S440 and S450 include:
s441, calculating a second current average value of a stable waveform part of a signal waveform diagram of the second electric signal, and making a straight line parallel to the X axis through a point corresponding to the second current average value, and marking the straight line as a starting reference line L2;
s442, selecting an intersection point of the starting reference line L2 and the stable waveform part of the signal waveform diagram, namely an ending time T2;
s451, the start time T1 and the end time T2 are subtracted to obtain the response time T.
Specifically, after the electric thruster is started, the working medium gas is ionized to generate plasma plumes, so that an electric signal generated by collecting an optical signal generated by ionization through the avalanche photodiode can show a trend of rising, falling and finally stabilizing.
In this embodiment, the stable waveform portion of the signal waveform of the second electrical signal is summed and a second current average value is taken, a straight line parallel to the X axis of the signal waveform is made at a point corresponding to the second current average value, and the straight line is denoted as the start reference line L2.
Because the current signal collected from the ignition start of the thruster is a signal which rises and then falls smoothly due to the influence of the power frequency noise, the intersection point of the starting reference line L2 and the first time when the second electric signal is stable is taken as the end time T2 of the electric thruster, and it can be seen from fig. 3 that t2=17.2 ms.
The difference between the time corresponding to the start time T1 and the time corresponding to the end time T2, i.e., t=t2-T1, is calculated as shown in fig. 3, and t=18.9 ms.
As shown in fig. 4, in one embodiment of the present application, a detection system suitable for measuring response time of an electric thruster is applied to any one of the detection methods for measuring response time of an electric thruster, where the detection system for measuring response time of an electric thruster includes an electric thruster 1, a vacuum environment simulator 2, a regulating assembly 3, a driving assembly 4, and a collecting assembly 5.
The vacuum environment simulation device 2 is used for simulating a vacuum environment. The adjusting component 3 comprises a first sliding table 301 extending towards the first direction, a second sliding table 302 extending towards the second direction, a third sliding table 303 extending towards the third direction and a coupler 304, wherein the first sliding table 301 is fixedly connected with the second sliding table 302, the third sliding table 302 is fixedly connected with the second sliding table 302, and the coupler 304 is fixedly connected between the first sliding tables 301. The driving assembly 4 comprises a first motor 401, a second motor 402 and a third motor 403, the first motor 401 is fixedly connected to one end of the first sliding table 301, the second motor 402 is fixedly connected to one end of the second sliding table 302, and the third motor 403 is fixedly connected to one end of the third sliding table 303. The collection assembly 5 comprises an avalanche photodiode 501, a collection circuit 502, a discharge circuit 503 and an oscilloscope 504, wherein the avalanche photodiode 501 is fixedly connected to the driving assembly 4, one end of the collection circuit 502 is electrically connected with the avalanche photodiode 501, one end of the discharge circuit 503 is electrically connected with the electric thruster 1, and the oscilloscope 504 is electrically connected with the collection circuit 502 and the discharge circuit 503.
Specifically, the first direction, the second direction and the third direction are perpendicular to each other, and a three-dimensional Cartesian coordinate system is formed.
The number of the first sliding tables 301 may be two, and the second sliding table 302 is fixedly connected between the two groups of the first sliding tables 301.
In this embodiment, the vacuum environment simulator 2 simulates a vacuum environment, the first motor 401 may push the first sliding table 301 to move, the second motor 402 may push the second sliding table 302 to move, and the third motor 403 may push the third sliding table 303 to move, so as to adjust the distance and angle between the electric thruster 1 and the avalanche photodiode 501, collect optical signals through the avalanche photodiode 501 and convert the optical signals into electrical signals, and collect discharge current signals and converted electrical signals through the collection circuit 502, the discharge circuit 503 and the oscilloscope 504, respectively.
As shown in fig. 5, in an embodiment of the present application, the detection system for measuring response time of the electric thruster further comprises an electric thruster holder 6 and a diode holder 7:
the electric thruster 1 is fixedly connected to one end of the electric thruster fixer 6, and the other end of the electric thruster fixer 6 is fixedly connected to one end of the third sliding table 303. The avalanche photodiode 501 is fixedly connected to one end of the diode holder 7, and the other end of the diode holder 7 is fixedly connected to the vacuum environment simulation device 2.
Specifically, the vacuum environment simulation apparatus 2 is a sealed light-free apparatus, and the influence of the ambient light on the experiment may be eliminated.
In this embodiment, the avalanche photodiode 501 is fixedly connected to the vacuum environment simulation apparatus 2 through the diode holder 7, and the electric thruster 1 is fixedly connected to the adjustment assembly 3 through the electric thruster holder 6, so that the position of the electric thruster 1 can be adjusted, thereby adjusting the positions of the electric thruster 1 and the avalanche photodiode 501 to a proper position.
As shown in fig. 6, in an embodiment of the present application, the detection system for measuring response time of an electric thruster further includes a shielding assembly 8, the shielding assembly 8 includes a shielding shell 801 and a shielding transparent shell 802, one end of the shielding shell 801 is fixedly connected to one end of the third sliding table 303, the shielding transparent shell 802 is fixedly connected to the other end of the shielding shell 801, and the avalanche photodiode 501 is fixedly connected to the inside of the shielding shell 801.
Specifically, for the vacuum environment simulation apparatus 2 in which the observation window is installed, there is one ambient light source. The photodiode is opposite to the ambient light source, so that the influence of the ambient light can be well shielded. As shown in fig. 6, the specific image of the design of the shielding assembly 8 is that the shielding transparent shell 802 on the front side is transparent, and the other shielding shells 801 are made of light shielding materials, so that the influence of ambient light is well shielded while the collected light signals are not interfered.
In this embodiment, the contact between the avalanche photodiode 501 and the external ambient light is isolated by the shielding shell 801, so as to avoid the interference of the ambient light, and the shielding transparent shell 802 ensures that the avalanche photodiode 501 can normally collect the optical signal, so as to avoid affecting the normal operation of the avalanche photodiode 501.
As shown, in an embodiment of the present application, the collecting circuit 502 is electrically connected to the collecting circuit sampling resistor 10, and the discharging circuit 503 is electrically connected to the discharging circuit sampling resistor 9.
In this embodiment, the voltage across the sampling resistor 10 and the voltage across the sampling resistor 9 are acquired by an oscilloscope.
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 foregoing examples illustrate only a few embodiments of the application and are described in detail herein without thereby limiting the scope of the application. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. Accordingly, the scope of the application should be assessed as that of the appended claims.
Claims (6)
1. A method of operation of an electric thruster response time measurement, the method of operation of an electric thruster response time measurement comprising:
configuring hardware equipment, starting an avalanche photodiode, and moving the avalanche photodiode to enable the avalanche photodiode to enter a working position;
starting an electric thruster, applying discharge high voltage to the electric thruster, and collecting a discharge current signal;
collecting the optical signal by an avalanche photodiode;
preprocessing the discharge current signal and the optical signal, and calculating the response time of the electric thruster according to the preprocessed discharge current signal and the preprocessed optical signal;
the starting of the electric thruster, applying discharge high voltage to the electric thruster, collecting discharge current signals, and comprises the following steps:
starting an electron source of the electric thruster to provide neutral gas;
starting a high-voltage power supply, applying the high-voltage power supply to the electric thruster, and collecting a discharge current signal of the electric thruster, and recording the discharge current signal as a first electric signal;
the preprocessing of the discharge current signal and the optical signal, and the calculation of the response time of the electric thruster according to the preprocessed discharge current signal and optical signal, comprises the following steps:
collecting optical signals in plasma beam generated by an electric thruster through an avalanche photodiode, converting the optical signals into electric signals, collecting the converted electric signals, and recording the electric signals as second electric signals;
closing the hardware equipment, and performing smoothing processing on the first electric signal and the second electric signal;
calculating a discharge reference line L1 of a signal waveform diagram of the first electric signal, and extracting a starting moment T1;
calculating a starting reference line L2 of a signal waveform diagram of the second electric signal, and extracting an ending time T2;
calculating response time T according to the response time T1 and the ending time T2;
the calculating the discharge reference line L1 of the signal waveform diagram of the first electric signal and extracting the starting time T1 includes:
calculating a first current average value before the thruster discharges in a signal waveform diagram of the first electric signal, and making a straight line parallel to an X axis by a point corresponding to the first current average value, and marking the straight line as a discharge reference line L1;
selecting the intersection point of the discharge reference line L1 and the last discharge current signal, namely starting time T1;
the calculating the starting reference line L2 of the signal waveform diagram of the second electrical signal, and extracting the ending time T2 includes:
calculating a second current average value of a stable waveform part of a signal waveform chart of the second electric signal, and making a straight line parallel to the X axis by a point corresponding to the second current average value, and marking the straight line as a starting reference line L2;
selecting an intersection point of the starting reference line L2 and a stable waveform part of the signal waveform diagram, namely an ending moment T2;
and (5) making a difference between the starting time T1 and the ending time T2 to obtain response time T.
2. The method of claim 1, wherein configuring the hardware device to activate the avalanche photodiode, and moving the avalanche photodiode into an operational position comprises:
connecting a hardware circuit to simulate a vacuum environment;
applying a bias voltage to the avalanche photodiode;
the distance and angle of the avalanche photodiode from the electric thruster are adjusted.
3. A detection system for electric thruster response time measurement, characterized by being applied to a method for operating an electric thruster response time measurement according to any one of claims 1 to 2, said detection system for electric thruster response time measurement comprising:
an electric thruster;
the vacuum environment simulation device is used for simulating a vacuum environment;
the adjusting assembly comprises a first sliding table extending towards the first direction, a second sliding table extending towards the second direction, a third sliding table extending towards the third direction and a coupler, wherein the first sliding table is fixedly connected with the second sliding table, the third sliding table is fixedly connected with the second sliding table, and the coupler is fixedly connected between the first sliding tables;
the driving assembly comprises a first motor, a second motor and a third motor, wherein the first motor is fixedly connected to one end of the first sliding table, the second motor is fixedly connected to one end of the second sliding table, and the third motor is fixedly connected to one end of the third sliding table;
the collecting assembly comprises an avalanche photodiode, a collecting loop, a discharging loop and an oscilloscope, wherein the avalanche photodiode is fixedly connected to the driving assembly, one end of the collecting loop is electrically connected with the avalanche photodiode, one end of the discharging loop is electrically connected with the electric thruster, and the oscilloscope is electrically connected with the collecting loop and the discharging loop.
4. The electrical thruster response time measurement detection system of claim 3, further comprising:
the electric thruster fixer is connected to one end of the electric thruster fixer, and the other end of the electric thruster fixer is fixedly connected to one end of the third sliding table;
the avalanche photodiode is fixedly connected to one end of the diode fixer, and the other end of the diode fixer is fixedly connected to the vacuum environment simulation device.
5. The system for detecting a measurement of a response time of an electric thruster of claim 4, further comprising:
the shielding assembly comprises a shielding shell and a shielding transparent shell, one end of the shielding shell is fixedly connected with one end of the third sliding table, the shielding transparent shell is fixedly connected with the other end of the shielding shell, and the avalanche photodiode is fixedly connected with the inside of the shielding shell.
6. The system of claim 5, wherein the acquisition loop is electrically connected to an acquisition loop sampling resistor, and the discharge loop is electrically connected to a discharge loop sampling resistor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311189089.6A CN116930668B (en) | 2023-09-15 | 2023-09-15 | Detection system and operation method for measuring response time of electric thruster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311189089.6A CN116930668B (en) | 2023-09-15 | 2023-09-15 | Detection system and operation method for measuring response time of electric thruster |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116930668A CN116930668A (en) | 2023-10-24 |
| CN116930668B true CN116930668B (en) | 2023-12-05 |
Family
ID=88377446
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311189089.6A Active CN116930668B (en) | 2023-09-15 | 2023-09-15 | Detection system and operation method for measuring response time of electric thruster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116930668B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117572136A (en) * | 2024-01-16 | 2024-02-20 | 国科大杭州高等研究院 | Detection system suitable for measuring response time of electric thruster |
| CN117590140B (en) * | 2024-01-18 | 2024-06-14 | 国科大杭州高等研究院 | Measurement method suitable for measuring response time of electric thruster and readable storage medium |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001092897A2 (en) * | 2000-05-31 | 2001-12-06 | Sri International | Systems and methods employing micro-fabricated field emission devices to sense and control potential differences between a space object and its space plasma environment, to emit charge from a space object, and in use with an electrodynamic tether to adjust an orbit of an orbiting space object |
| CN1329463A (en) * | 2000-06-16 | 2002-01-02 | 株式会社村田制作所 | Load control type exciter |
| US7168330B1 (en) * | 2006-06-07 | 2007-01-30 | Northrop Grumman Corporation | Multi-parametric media transducer |
| CN103994006A (en) * | 2014-06-13 | 2014-08-20 | 天津大学 | Fuel injector needle valve response time measuring system and measuring method |
| CN105781920A (en) * | 2016-04-28 | 2016-07-20 | 中国人民解放军国防科学技术大学 | Magnetic plasma thrustor supported through lasers |
| CN108036888A (en) * | 2017-11-24 | 2018-05-15 | 电子科技大学 | Micromass cell culture device based on torsional pendulum type |
| CN111149141A (en) * | 2017-09-04 | 2020-05-12 | Nng软件开发和商业有限责任公司 | Method and apparatus for collecting and using sensor data from a vehicle |
| CN114218750A (en) * | 2021-11-16 | 2022-03-22 | 中国人民解放军战略支援部队航天工程大学 | Satellite-borne micro thruster thrust response time measuring method based on digital filter |
| CN114527689A (en) * | 2022-01-14 | 2022-05-24 | 沈阳航天新光集团有限公司 | Electromagnetic valve measurement and control system for spaceflight |
| CN115389212A (en) * | 2022-08-31 | 2022-11-25 | 国科大杭州高等研究院 | System and method for detecting starting response time of cold air thruster |
| CN115655732A (en) * | 2022-09-30 | 2023-01-31 | 国科大杭州高等研究院 | Cold air thrust response test data processing method, device, equipment and readable medium |
| CN115681063A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Operation method of multi-working-mode Hall propulsion system |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120170024A1 (en) * | 2009-09-22 | 2012-07-05 | Medhat Azzazy | Long Range Acquisition and Tracking SWIR Sensor System Comprising Micro-Lamellar Spectrometer |
| FR2997462B1 (en) * | 2012-10-30 | 2018-09-14 | Safran Aircraft Engines | SUPPLYING AN ION PROPELLANT IN PROPULSIVE GAS |
| US9110169B2 (en) * | 2013-03-08 | 2015-08-18 | Advanced Scientific Concepts, Inc. | LADAR enabled impact mitigation system |
| EP3289430B1 (en) * | 2015-04-27 | 2019-10-23 | Snap-Aid Patents Ltd. | Estimating and using relative head pose and camera field-of-view |
| WO2017149526A2 (en) * | 2016-03-04 | 2017-09-08 | May Patents Ltd. | A method and apparatus for cooperative usage of multiple distance meters |
-
2023
- 2023-09-15 CN CN202311189089.6A patent/CN116930668B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001092897A2 (en) * | 2000-05-31 | 2001-12-06 | Sri International | Systems and methods employing micro-fabricated field emission devices to sense and control potential differences between a space object and its space plasma environment, to emit charge from a space object, and in use with an electrodynamic tether to adjust an orbit of an orbiting space object |
| CN1329463A (en) * | 2000-06-16 | 2002-01-02 | 株式会社村田制作所 | Load control type exciter |
| US7168330B1 (en) * | 2006-06-07 | 2007-01-30 | Northrop Grumman Corporation | Multi-parametric media transducer |
| CN103994006A (en) * | 2014-06-13 | 2014-08-20 | 天津大学 | Fuel injector needle valve response time measuring system and measuring method |
| CN105781920A (en) * | 2016-04-28 | 2016-07-20 | 中国人民解放军国防科学技术大学 | Magnetic plasma thrustor supported through lasers |
| CN111149141A (en) * | 2017-09-04 | 2020-05-12 | Nng软件开发和商业有限责任公司 | Method and apparatus for collecting and using sensor data from a vehicle |
| CN108036888A (en) * | 2017-11-24 | 2018-05-15 | 电子科技大学 | Micromass cell culture device based on torsional pendulum type |
| CN114218750A (en) * | 2021-11-16 | 2022-03-22 | 中国人民解放军战略支援部队航天工程大学 | Satellite-borne micro thruster thrust response time measuring method based on digital filter |
| CN114527689A (en) * | 2022-01-14 | 2022-05-24 | 沈阳航天新光集团有限公司 | Electromagnetic valve measurement and control system for spaceflight |
| CN115389212A (en) * | 2022-08-31 | 2022-11-25 | 国科大杭州高等研究院 | System and method for detecting starting response time of cold air thruster |
| CN115655732A (en) * | 2022-09-30 | 2023-01-31 | 国科大杭州高等研究院 | Cold air thrust response test data processing method, device, equipment and readable medium |
| CN115681063A (en) * | 2023-01-03 | 2023-02-03 | 国科大杭州高等研究院 | Operation method of multi-working-mode Hall propulsion system |
Non-Patent Citations (2)
| Title |
|---|
| 华卫令,马东堂,魏急波.基于小波变换的雪崩光电二极管信号检测方法.中国激光.2004,全文. * |
| 王启明 ; 姜燕冰 ; 张秀达 ; 严惠民 ; .采集强干扰下微弱信号的APD电路系统研究.光子学报.2008,全文. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116930668A (en) | 2023-10-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN116930668B (en) | Detection system and operation method for measuring response time of electric thruster | |
| US6870157B1 (en) | Time-of-flight mass spectrometer system | |
| EP0328869B1 (en) | Electron beam testing of electronic components | |
| CA1220559A (en) | Noncontact dynamic tester for integrated circuits | |
| US4314156A (en) | Automated mass spectrometer analysis system | |
| US4292519A (en) | Device for contact-free potential measurements | |
| CN110687444A (en) | Device and method for testing switching-on and switching-off average speed of 10kV vacuum circuit breaker | |
| EP0559202B1 (en) | Secondary ion mass spectrometer for analyzing positive and negative ions | |
| JPS63269445A (en) | Electron beam head | |
| US5715049A (en) | Light measuring apparatus for quantifying photons | |
| EP1329700A1 (en) | Optical measurement apparatus and method for optical measurement | |
| US5146089A (en) | Ion beam device and method for carrying out potential measurements by means of an ion beam | |
| EP0299465A2 (en) | An apparatus for sampling, analyzing and displaying an electrical signal | |
| CN111175774B (en) | Control method of TOF sensor module | |
| GB2183898A (en) | Checking voltages in integrated circuit by means of an electron detector | |
| EP0209236B1 (en) | Electron beam testing of integrated circuits | |
| McBride et al. | Integrated measurement system for high speed unsteady plasma flow and its application to electric arcs | |
| Bond et al. | A wide aperture high gain beam profile scanner | |
| Hedfjaell et al. | Electrooptical ion detector for gas chromatography/mass spectrometry | |
| JPS6329788B2 (en) | ||
| JP2685306B2 (en) | Beam position monitor for particle accelerator | |
| CN116973702B (en) | Signal identification method and system applied to GIS partial discharge test | |
| CN221042815U (en) | Simulated micronucleus pulse generator | |
| Alcorta et al. | Status of the Machine Protection System for ARIEL E-linac | |
| JP2001144155A (en) | Semiconductor analysis device and analysis method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |