CN115453241A - Batch diagnosis test system for electric thrusters - Google Patents
Batch diagnosis test system for electric thrusters Download PDFInfo
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- CN115453241A CN115453241A CN202211072268.7A CN202211072268A CN115453241A CN 115453241 A CN115453241 A CN 115453241A CN 202211072268 A CN202211072268 A CN 202211072268A CN 115453241 A CN115453241 A CN 115453241A
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Abstract
The application discloses batch electric thruster diagnosis test system includes: the vacuum subsystem provides a vacuum test environment for the thruster head, is used for fixing the thruster head based on an ignition tool and is connected to the atmospheric environment through an electrode; the test box is connected with the electrode of the vacuum subsystem, is provided with a sensor corresponding to the state parameter of the thruster head to be acquired, and transmits the acquired state parameter to the system host; and the system host is used for receiving the acquired state parameters, comparing the acquired state parameters with corresponding parameter thresholds, controlling the test environment to be stable under the condition that the requirements of the corresponding parameter thresholds are not met, and/or giving an alarm based on the corresponding state parameters. The batched electric thruster diagnosis and test system can replace testers to execute continuous test and measurement tasks of the electric thrusters in a severe test environment.
Description
Technical Field
The application relates to the technical field of spacecraft testing, in particular to a batch electric thruster diagnosis testing system.
Background
The propulsion system is an actuating mechanism of a spacecraft platform attitude and orbit control system, plasma propulsion (hereinafter referred to as an electric thruster) is the fastest technical direction for development and application in the field of space propulsion in recent years, and the micro vacuum arc thruster is one of the electric thrusters, generates plasma jet to form thrust by utilizing ionized metal steam between an anode and a cathode in vacuum, and is an ideal electric propulsion type which is most suitable for networking satellite application at present. So far, the test of the thruster head, one of the core components of the electric thruster for spacecraft, is still mainly in the small-batch manual control test record, and the problem points of the traditional method are as follows:
the prior method has the following problems in the test process:
the ignition test of the electric thruster can last hundreds of hours, and a tester cannot accompany the test and test recorded data all the time.
The data acquisition and recording are frequently carried out manually by personnel, and the test phenomenon is observed, so that the defect that the whole test process cannot be monitored completely in real time, the test data is not continuous, and the condition that important data are missed can be caused.
The vacuum subsystem, the tested temperature and humidity environment and the test circuit board can change along with the weather and the operation of equipment, and the related parameters such as the vacuum degree, the temperature and the humidity cannot be recorded more accurately by the conventional test means, so that the statistical analysis of the test result is not facilitated.
Disclosure of Invention
The embodiment of the application provides a batch diagnosis test system for an electric thruster, which is used for replacing a tester to execute continuous test measurement tasks of the electric thruster in a severe test environment.
The embodiment of the application provides a batch electric thruster diagnosis test system, includes:
the vacuum subsystem provides a vacuum test environment for the thruster head, is used for fixing the thruster head based on an ignition tool and is connected to the atmospheric environment through an electrode;
the test box is connected with the electrode of the vacuum subsystem, is provided with a sensor corresponding to the state parameters of the thruster head to be acquired, and transmits the acquired state parameters to the system host;
and the system host is used for receiving the acquired state parameters, comparing the acquired state parameters with corresponding parameter thresholds, controlling the test environment to be stable under the condition that the requirements of the corresponding parameter thresholds are not met, and/or giving an alarm based on the corresponding state parameters.
Optionally, the test kit further comprises a programmable power supply for supplying power to the test kit and each sensor.
Optionally, the test box is provided therein with a channel acquisition card 302, a surface-mount thermal resistance thermometer 303, a current and voltage acquisition sensor 308, and a plurality of test circuit boards 309;
any test circuit board 309 is connected with the programmable power supply, and is configured with a plurality of channels for outputting positive and negative electrodes, so as to supply power to a plurality of thruster heads and the current and voltage acquisition sensor 308;
the sensors of the surface-mounted thermal resistance thermometer 303 are attached to the test circuit boards 309 and the thruster head body for measuring temperature;
the current and voltage acquisition sensor 308 and the patch type thermal resistance thermometer 303 perform a/D conversion through the channel acquisition card 302, and transmit acquired data to a system host through a specified protocol.
Optionally, an ion blower 301 is further arranged in the test box, and is triggered to be turned on based on a control instruction to cool the diagnostic test system;
the test box face still is provided with: 220V power female plug 305, test circuit board power banana head 306, 12V power female plug 307, thruster cathode and anode power female plug 312, test box power supply indicator lamp 313, test box main switch 314 and portable handle 315.
Optionally, the system host is specifically configured to:
when the acquired current value is higher or lower than a preset current alarm threshold value, carrying out alarm prompt on a corresponding channel;
under the condition that the temperature measured by the surface-mounted thermal resistance temperature measuring instrument is higher than a preset temperature threshold value, the rotation speed of the ion fan is controlled to be increased through the controller;
under the condition that the value measured by the temperature and humidity sensor is higher or lower than a preset temperature and humidity threshold value, the controller controls the air conditioner to be started, and executes the corresponding function of the instruction packet, so that the test environment is in a relatively stable state;
and under the condition that the numerical value measured by the vacuum degree sensor is higher or lower than a preset vacuum degree threshold value, performing vacuum degree alarm prompting.
Optionally, the programmable power supply unit is provided with a bluetooth module to turn on and off the test system based on the bluetooth module, and send generated alarm information to the tester through the bluetooth module.
Optionally, the test system further comprises a display connected with the system host and used for presenting a test system interface based on the upper computer software.
The batched electric thruster diagnosis and test system can replace testing personnel to execute continuous test and measurement tasks of the electric thrusters in a severe test environment.
The foregoing description is only an overview of the technical solutions of the present application, and the present application can be implemented according to the content of the description in order to make the technical means of the present application more clearly understood, and the following detailed description of the present application is given in order to make the above and other objects, features, and advantages of the present application more clearly understandable.
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Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the application. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic diagram of an overall structure of an electric thruster diagnostic test system according to an embodiment of the present application;
FIG. 2 is a schematic structural diagram of a test box according to an embodiment of the present application;
FIG. 3 is a schematic diagram of a test box according to an embodiment of the present disclosure.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
The embodiment of the application provides a batch electric thruster diagnosis test system, as shown in fig. 1, including:
and the vacuum subsystem 1 is used for providing a vacuum test environment for the thruster head, fixing the thruster head based on an ignition tool and connecting the thruster head to the atmospheric environment through an electrode. Specifically, the vacuum subsystem 1 is used for providing a vacuum environment for a thruster head, the thruster head is fixed on an ignition tool, a cathode and an anode are connected with a copper electrode on an electrode flange inside a vacuum cabin of the vacuum subsystem, then the electrode penetrates through the flange to reach the atmosphere environment outside the cabin, and the copper electrode on the electrode flange 11 is connected with a power supply female plug of the thruster cathode and the anode of a test box, so that the purpose of supplying power for the thruster head is achieved.
The test box 3 is connected with the electrode of the vacuum subsystem, is provided with a sensor corresponding to the state parameter of the thruster head to be acquired, and transmits the acquired state parameter to the system host;
and the system host 5 is used for receiving the acquired state parameters, comparing the acquired state parameters with corresponding parameter thresholds, and controlling the test environment to be stable and/or giving an alarm based on the corresponding state parameters under the condition that the requirements of the corresponding parameter thresholds are not met. The upper computer (system host) is used for centralized control, the test process can be edited independently, and the process can be saved and called.
In some embodiments, a programmable power supply 4 is also included for powering the test chamber and the sensors. The programmable power supply 4 is used for supplying power for the test box, the current and voltage acquisition sensor, the patch type thermal resistance temperature measuring instrument and the like. In this application, the test box 3, the programmable power supply 4 and the system host 5 adopt a modular design, and a plurality of test boxes 3 can be arranged based on the cabinet, and in some specific scenes, the cabinet can be provided with rollers to carry out braking.
In some embodiments, the system further comprises a display 2 connected to the system host 5 for presenting a test system interface based on the upper computer software.
The batched electric thruster diagnosis and test system can replace testers to execute continuous test and measurement tasks of the electric thrusters in a severe test environment.
In some embodiments, as shown in fig. 2, the test box 3 has a channel acquisition card 302, a patch type thermal resistance thermometer 303, a current and voltage acquisition sensor 308, and a plurality of test circuit boards 309 disposed therein.
As shown in fig. 3, any test circuit board 309 is connected to the programmable power supply, and is configured with multiple channels for outputting positive and negative electrodes, so as to supply power to multiple thruster heads and the current and voltage collecting sensor 308;
the sensors of the surface-mounted thermal resistance thermometer 303 are attached to the test circuit boards 309 and the thruster head body for measuring temperature;
the current and voltage acquisition sensor 308 and the patch type thermal resistance thermometer 303 perform a/D conversion through the channel acquisition card 302, and transmit acquired data to a system host through a specified protocol.
In some embodiments, an ion blower 301 is further disposed in the test box, and is triggered to be turned on based on a control instruction to cool the diagnostic test system;
the test box face still is provided with: 220V power female plug 305, test circuit board power banana head 306, 12V power female plug 307, thruster cathode and anode power female plug 312, test box power supply indicator lamp 313, test box main switch 314 and portable handle 315.
Specifically, the test box is shown in fig. 2, the wiring schematic diagram is shown in fig. 3, and the test box mainly comprises an ion blower 301, a channel acquisition card 302, a patch type thermal resistance thermometer 303, an rs485 protocol port 304, a 220V power supply female plug 305, a test circuit board power supply banana head 306, a 12V power supply female plug 307, a current and voltage acquisition sensor 308, a test circuit board 309, a vent 310, a channel switch 311, a thruster cathode and anode power supply female plug 312, a test box power supply indicator 313, a test box main switch 314, a portable handle 315 and the like. In some specific scenes, the test circuit boards are powered, each test circuit board can output three channels of a positive electrode and a negative electrode (4 test circuit boards are arranged in the test box), the effect of simultaneously supplying power to 12 thruster heads is achieved through the current and voltage acquisition sensors, meanwhile, the sensors are attached to the circuit board and the thruster head body by the surface-mounted thermal resistance temperature measuring instrument for measuring the temperature, the current and voltage acquisition sensors and the temperature measuring instrument transmit acquired data to a system host through A/D conversion of the channel acquisition cards and an RS485 protocol, acquisition software operated by the system host is displayed and stored, and the ion fan cools the whole system.
In some embodiments, the system host 5 is specifically configured to:
when the collected current value is higher or lower than a preset current alarm threshold value, carrying out alarm prompt on a corresponding channel;
under the condition that the temperature measured by the patch type thermal resistance thermometer is higher than a preset temperature threshold, the controller controls the ion fan to increase the rotating speed;
under the condition that the value measured by the temperature and humidity sensor is higher or lower than a preset temperature and humidity threshold value, the controller controls the air conditioner to be started, and executes the corresponding function of the instruction packet, so that the test environment is in a relatively stable state;
and under the condition that the numerical value measured by the vacuum degree sensor is higher or lower than a preset vacuum degree threshold value, performing vacuum degree alarm prompting.
In specific application, the system host 5 is used for operating acquisition software, storing data transmitted by the channel acquisition card through A/D conversion through an RS485 protocol, reading back the stored data, displaying the data in a data list and a curve graph mode, and judging the data displayed by the current acquisition sensor, the patch type thermal resistance thermometer and the temperature and humidity sensor in real time:
if the current value is higher or lower than the early-stage set alarm threshold value, carrying out alarm prompt on the channel;
if the temperature measured by the surface mount type thermal resistance temperature measuring instrument is higher than a preset threshold value, the system sends a feedback signal to the ion fan through the controller, and the rotation speed of the ion fan is increased to achieve a rapid cooling effect;
if the value measured by the temperature and humidity sensor is higher or lower than a preset threshold value, the system sends a feedback signal to the air conditioner through the controller, and at the moment, the air conditioner can open a function corresponding to an instruction packet sent by the controller, so that the test environment is in a relatively stable state;
if the value measured by the vacuum degree sensor (a resistance gauge and an ionization gauge) 13 is higher or lower than a preset threshold value, the system can give an alarm for the vacuum degree;
the current clamp and the high-voltage differential probe are used for testing the current and the voltage of each channel in the conventional testing method, and the total price of the selected current clamp, the selected high-voltage differential probe and the oscilloscope is about ten times of the total price of the required sensors and other equipment according to the requirements on high reliability and high stability of spacecraft single-machine testing equipment. The scheme of the application adopts the scheme of including current and voltage acquisition sensors, a patch type thermal resistance thermometer, a vacuum degree sensor (a resistance gauge and an ionization gauge) and the like, and compared with the existing scheme of current clamps and high-voltage differential probes, the test cost can be reduced by about 90%. That is, the scheme of the application greatly reduces the test burden of enterprises.
Optionally, the programmable power supply unit is provided with a bluetooth module to turn on and off the test system based on the bluetooth module, and send generated alarm information to the tester through the bluetooth module.
The power supply unit and the programmable power supply unit of the whole set of system are provided with the Bluetooth module, manual control and remote Bluetooth can be used for controlling the startup and shutdown of the test system, and alarm information generated by the system can be sent to relevant responsible testers through the Bluetooth module.
The electric thruster diagnosis test system can replace testers to execute continuous test measurement tasks of the electric thruster in a severe test environment. This application complete equipment height integrated and modularization are installed in standard test rack, and the rack takes the gyro wheel area brake. All the devices are controlled in a centralized mode through an upper computer (a system host), the test process can be edited independently, and the process can be stored and called. The data acquisition interval can be set, the data is stored in real time, and the alarm threshold range can be set. The data stored in the application can be read back and can be displayed in a data list and a curve graph mode. The temperature monitoring and testing device can continuously monitor and record the temperature values of the vacuum subsystem, the temperature and humidity environment and the testing circuit and store the temperature values, and can ensure the accuracy of the testing result to a certain extent. The method can also be applied to screening tests of the thruster head, and the states (including short circuit, open circuit and normal) of the thruster head can be judged according to a preset alarm threshold value.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one of 8230, and" comprising 8230does not exclude the presence of additional like elements in a process, method, article, or apparatus comprising the element.
The above-mentioned serial numbers of the embodiments of the present application are merely for description and do not represent the merits of the embodiments.
Through the description of the foregoing embodiments, it is clear to those skilled in the art that the method of the foregoing embodiments may be implemented by software plus a necessary general hardware platform, and certainly may also be implemented by hardware, but in many cases, the former is a better implementation. Based on such understanding, the technical solutions of the present application may be embodied in the form of a software product, which is stored in a storage medium (e.g., ROM/RAM, magnetic disk, optical disk) and includes instructions for enabling a terminal (e.g., a mobile phone, a computer, a server, or a network device) to execute the method according to the embodiments of the present application.
While the present embodiments have been described with reference to the accompanying drawings, it is to be understood that the present embodiments are not limited to those precise embodiments, which are intended to be illustrative rather than restrictive, and that various changes and modifications may be effected therein by one skilled in the art without departing from the scope of the appended claims.
Claims (7)
1. A batch electric thruster diagnostic test system, comprising:
the vacuum subsystem provides a vacuum test environment for the thruster head, is used for fixing the thruster head based on an ignition tool and is connected to the atmospheric environment through an electrode;
the test box is connected with the electrode of the vacuum subsystem, is provided with a sensor corresponding to the required state parameter of the thruster head and transmits the acquired state parameter to the system host;
and the system host is used for receiving the acquired state parameters, comparing the acquired state parameters with corresponding parameter thresholds, controlling the test environment to be stable under the condition that the requirements of the corresponding parameter thresholds are not met, and/or giving an alarm based on the corresponding state parameters.
2. The batched electric thruster diagnostic test system of claim 1, further comprising a programmable power supply for powering the test chamber and the sensors.
3. The batched electric thruster diagnostic test system of claim 2, wherein the test box is provided with a channel acquisition card (302), a patch type thermal resistance thermometer (303), a current and voltage acquisition sensor (308) and a plurality of test circuit boards (309);
any test circuit board (309) is connected with the programmable power supply and is provided with a plurality of channels for outputting positive and negative electrodes so as to supply power to a plurality of thruster heads and a current and voltage acquisition sensor (308);
the sensor of the patch type thermal resistance temperature measuring instrument (303) is attached to each test circuit board (309) and the thruster head body for measuring the temperature;
the current and voltage acquisition sensor (308) and the patch type thermal resistance thermometer (303) perform A/D conversion through the channel acquisition card (302), and transmit acquired data to a system host through a specified protocol.
4. The batched electric thruster diagnostic test system of claim 3, wherein an ion blower (301) is further arranged in the test box and is used for triggering to be started based on a control instruction so as to cool the diagnostic test system;
the test box face still is provided with: the device comprises a 220V power supply female plug (305), a test circuit board power supply banana head (306), a 12V power supply female plug (307), a thruster cathode and anode power supply female plug (312), a test box power supply indicator lamp (313), a test box main switch (314) and a portable handle (315).
5. The batched electric thruster diagnostic test system of claim 4, wherein the system host is specifically configured to:
when the collected current value is higher or lower than a preset current alarm threshold value, carrying out alarm prompt on a corresponding channel;
under the condition that the temperature measured by the patch type thermal resistance thermometer is higher than a preset temperature threshold, the controller controls the ion fan to increase the rotating speed;
under the condition that the numerical value measured by the temperature and humidity sensor is higher or lower than a preset temperature and humidity threshold value, the controller controls the air conditioner to be started, and executes the corresponding function of the instruction packet, so that the test environment is in a relatively stable state;
and under the condition that the numerical value measured by the vacuum degree sensor is higher or lower than a preset vacuum degree threshold value, performing vacuum degree alarm prompting.
6. The batched electric thruster diagnostic test system of claim 2, wherein the programmable power unit is provided with a bluetooth module to turn on and off the test system based on the bluetooth module, and the generated alarm information is sent to a tester through the bluetooth module.
7. The batched electric thruster diagnostic test system of claim 1, further comprising a display coupled to the system host for presenting a test system interface based on host computer software.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211072268.7A CN115453241A (en) | 2022-09-02 | 2022-09-02 | Batch diagnosis test system for electric thrusters |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211072268.7A CN115453241A (en) | 2022-09-02 | 2022-09-02 | Batch diagnosis test system for electric thrusters |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117647682A (en) * | 2023-10-30 | 2024-03-05 | 遨天科技(北京)有限公司 | Electric thruster life prediction method and device |
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2022
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| CN101539483A (en) * | 2009-04-29 | 2009-09-23 | 北京航空航天大学 | Electric propulsion testing platform measurement control device |
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| CN106680612A (en) * | 2015-11-11 | 2017-05-17 | 北京卫星环境工程研究所 | Performance test device for emitter of field emission electric thruster of satellite |
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