CN114527689A - Electromagnetic valve measurement and control system for spaceflight - Google Patents
Electromagnetic valve measurement and control system for spaceflight Download PDFInfo
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- CN114527689A CN114527689A CN202210041356.4A CN202210041356A CN114527689A CN 114527689 A CN114527689 A CN 114527689A CN 202210041356 A CN202210041356 A CN 202210041356A CN 114527689 A CN114527689 A CN 114527689A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24215—Scada supervisory control and data acquisition
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
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Abstract
The invention discloses an electromagnetic valve measurement and control system for spaceflight, wherein a thruster and an electromagnetic valve are assembled into an engine, the engine is fixed on a test frame, a pressure sensor is connected to the thruster, a vibration sensor is fixed on an engine bracket, a temperature sensor is adhered to the thruster, control cables of the pressure sensor, the vibration sensor and the temperature sensor are connected to the electromagnetic valve measurement and control system, the electromagnetic valve measurement and control system is in signal connection with a computer, the electromagnetic valve measurement and control system adopts an NI USB6210 controller, and the NI USB6210 controller collects and stores field signals and outputs control signals. According to the invention, the opening and closing response of the electromagnetic valve can be acquired by introducing the closed loop. The electromagnetic valve acquisition system can adapt to some occasions of field data acquisition and off-line use, is not limited by time and space, and is flexible and practical.
Description
Technical Field
The invention relates to the technical field of rocket engine electromagnetic valve measurement and control, in particular to an aerospace electromagnetic valve measurement and control system.
Background
The automation degree of the launching of the novel carrier rocket needs to adopt a large number of electromagnetic valves for controlling the opening and closing of the engine. With the continuous breakthrough of the technical problem in the aerospace field in China, the requirement on the quality of the rocket is increasingly promoted. The rocket engine is the core of a rocket power system, the electromagnetic valve is one of important parts of the rocket engine, in particular to an attitude and orbit control power system mainly based on a liquid power system, and the attitude and orbit control system mainly completes the tasks of orbital transfer and orbital entry, wherein the tasks of climbing and changing the inclination angle of the orbit are also included to eliminate attitude static errors, so that a satellite flies according to a preset attitude and orbit, the performance of the satellite is ensured, and the flying task is completed. The opening response of the solenoid valve determines the engine cranking time and the closing response determines the consumption of entrained propellant. The response time of opening and closing of the electromagnetic valve can be reasonably tested, and the response time is very important for system design. The existing control system cannot acquire the closing response state of the electromagnetic valve, and the acquisition system is large in size and inconvenient to carry.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a measuring and controlling system of an electromagnetic valve for spaceflight, and the set of control system mainly completes high-precision time sequence control. Meanwhile, the system has the functions of starting, emergency shutdown, program recoding, valve current acquisition, data processing and the like.
The technical scheme includes that the aerospace electromagnetic valve measurement and control system is characterized in that an engine is assembled by a thruster and an electromagnetic valve, the engine is fixed on a test frame, a pressure sensor is connected to the thruster, a vibration sensor is fixed on an engine support, a temperature sensor is pasted on the thruster, control cables of the pressure sensor, the vibration sensor and the temperature sensor are connected to the electromagnetic valve measurement and control system, the electromagnetic valve measurement and control system is in signal connection with a computer, the electromagnetic valve measurement and control system adopts an NIUSB6210 controller, and the NIUSB6210 controller collects and stores field signals and outputs control signals.
Furthermore, the control signal output by the NI USB6210 controller is output to the optical coupler isolator in a digital quantity mode, the control signal is amplified by the optical coupler isolator and then output to the electromagnetic valve interface, the electromagnetic valve interface outputs a current signal to the current sensor, and the current sensor outputs a 0-10V voltage signal to the analog quantity input end of the NI USB6210 controller.
Furthermore, the power supply of the electromagnetic valve measurement and control system is divided into two paths, and one path of the power supply introduces a bipolar linear power supply and a unipolar switching power supply to supply power for the current sensor and the pressure sensor; and the other path is externally connected with a power supply through a panel driving interface to supply power to the valve.
The invention has the beneficial effects that: according to the invention, the opening and closing response of the electromagnetic valve can be acquired by introducing the closed loop. The electromagnetic valve measurement and control system is a miniaturized control and recoding system which is mainly established for completing polarity and response tests of single or multiple electromagnetic valves, and the control system mainly completes high-precision time sequence control. Meanwhile, the system has the functions of starting, emergency shutdown, program recoding, valve current acquisition, data processing and the like.
The portable electromagnetic valve acquisition system can adapt to some occasions of field data acquisition and offline use. It is battery powered, communicates with the computer, has its own internal memory, stores a certain amount of data, and transmits the data to the computer at the appropriate time. The device has certain programming capability and can become a device with complete functions by being matched with an application program, thereby meeting the application requirements of different occasions, not needing to increase the field, not being limited by time and space, and being flexible and practical.
Drawings
FIG. 1 is a schematic diagram of an electromagnetic valve measurement and control system for aerospace of the invention.
FIG. 2 is a circuit diagram of a first solenoid valve closing characteristic curve measurement mode.
FIG. 3 is a circuit diagram of a second measurement mode of the closing characteristic curve of the solenoid valve.
FIG. 4 is a data processing diagram of the present invention.
FIG. 5 is a current response diagram of the solenoid valve of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein can be arranged and designed in a wide variety of different configurations.
The electromagnetic valve acquisition control system realizes a data acquisition and control system based on a virtual instrument technology and a USB bus by combining the current advanced computer measurement and control technology according to the test requirements. The design realizes the measurement and control system integrating multiple functions of signal acquisition, record storage and the like. The software system comprises a Windows system, an NI programmable intelligent IO card, a software development platform Labview, a module driver, application software and the like.
The system comprises a portable measurement and control case, a control system platform, a system controller, a collection board card, a control output board card, a power supply field sensor power supply and a plug panel, and comprises quick aerial plugs and other connectors, sensors, a Hall current sensor, a relay, a solid-state relay, an isolation module, an isolation conversion module, a connecting cable, a power supply cable, an internal cable and a field cable. The valve acquisition control system is based on an NI platform, and realizes the acquisition and storage work of field signals and the output control work of field control signals by using an NI USB6210 controller.
The system adopts a 220V power supply for power supply, a control cable of the sensor is connected into the system through a sensor interface, and an acquired signal is input into an acquisition card in an analog quantity mode and fed back to a computer. The computer measurement and control software is used for controlling, the control signal is transmitted to the acquisition card and is output to the optical coupler isolator in a digital quantity mode, and the optical coupler isolator is used for amplifying the signal and protecting the acquisition card. Because the input and the output of the optocoupler relay are mutually isolated, the electrical signal transmission has the characteristics of unidirectionality and the like, thereby having good electrical insulation capability and anti-interference capability. And because the input end of the optical coupler belongs to a low-resistance element working in a current mode, the optical coupler has strong common-mode rejection capability. The digital communication and real-time control in the control system are used as interface devices for signal isolation, so that the working reliability of the system can be greatly improved. The signal one-way transmission, input and output have realized electrical isolation completely, and output signal does not have the influence to the input, and the interference killing feature is strong, job stabilization, contactless, long service life, transmission efficiency is high. And transmitting the control signal to the solenoid valve interface.
The valve acquisition control system is divided into two paths of power supply, one path of power supply is introduced into a bipolar linear power supply and a unipolar switching power supply, and the bipolar linear power supply and the unipolar switching power supply are responsible for supplying power to a Hall sensor and a terminal pressure sensor in the system; and the other path of external power supply is externally connected with a power supply through a panel driving interface and is responsible for supplying power to the valve. And after the system is normally started, software is started to start data acquisition control.
Testing solenoid valve operating response time
Powering up a system: the AC was first connected to a 220V supply socket (the AC socket has a built-in fuse and a backup fuse for replacement).
Valve power supply: the driving interface is connected with a TGG push-pull type rapid aviation plug.
Communication connection: a double male USB3.0 which is respectively connected with the computer case communication port and the computer USB port.
The software uses: double-clicking an acquisition control system icon, opening a test bed acquisition control system, performing a test, and withdrawing the system after the test is completed; and double clicking the DataReview data playback icon, performing offline analysis processing on the data, and generating a data report. And (3) system power-off: the computer system is first turned off and then pulled out of the power supply socket according to the power-on switch- > AC plug. All control and signal acquisition of the system are completed by adopting quick connectors, and the connectors are distributed on a front panel of the test case. The valve on the panel controls the output, the pressure acquisition adopts the common military grade J30J-15ZKP45/J30J-21ZKP45 to electrically connect the connector,
the electromagnetic valve closing characteristic curve measuring mode is adopted, when an engine is shut down, namely the electromagnetic valve coil is powered off, according to Lenz's law, the coil can generate reverse electromotive force at the moment. By measuring the voltage drop or the loop current generated by the back electromotive force, the closing characteristic of the electromagnetic valve can be analyzed. The diode has the electrical characteristics of forward conduction and reverse cut-off, and the forward resistance is reduced along with the increase of voltage and current, so 2 circuits can be built for analysis: as shown in fig. 2-3, two measurement modes,
fig. 2 shows a first schematic principle, when the power switch is closed, the coil works normally, and the diode is in a cut-off state. At the moment of engine shutdown and the moment of switch disconnection, the coil generates reverse induced electromotive force, the diode is conducted, the coil, the resistor and the diode form an independent closed electric loop, and the change state of the loop circuit can be detected through the current tester, namely the current change state of the coil.
Fig. 3 shows a second scheme principle, when the power switch is closed, the coil works normally, and the diode is in a cut-off state. At the moment of shutting down the engine and the moment of disconnecting the switch, the coil generates reverse induced electromotive force, the diode is conducted, at the moment, the coil, the resistor and the diode form an independent closed electric loop, and the voltage drop change state of two ends of the resistor in the loop can be measured through the current sensor, so that the current change state of the coil can be obtained.
And (4) mounting the thruster and the electromagnetic valve to assemble the engine. And placing the engine on a test frame for fixing. A pressure sensor interface connecting the forcer to the thruster; mounting a vibration sensor on an engine mount; and sticking a temperature sensor to the thruster, and accessing the thruster to an electromagnetic measurement and control system. And connecting the measurement and control system with a computer. Before electrifying, checking whether the connection of the sensor cable is normal, whether the power supply of the sensor and the connection of the signal cable are normal, and whether the connection of the power supply cable is normal. The control cabinet is powered on, the power switch is pressed down, the power indicator lights are turned on blue at the moment, and the system is powered on normally. And an external drive adjustable power supply is connected. And connecting the field signal cable into a corresponding plugging area, and starting the computer to enter software operation. And loading a preset pulse program into system software, starting the system software, then carrying out electromagnetic valve work and data real-time acquisition, and closing the control computer after the test is finished. The starting switch is pressed down, and the indicator light is turned off. The field patch cable is disconnected.
The open-close curve of the electromagnetic valve is shown in fig. 4-5, according to the conventional system, the open pressure of the electromagnetic valve can be tested, but the electromagnetic valve is closed to respond, and the system cannot be switched off, so that the closed loop is introduced into the system, circuit loop current exists in the whole set of measurement and control system, and the electromagnetic valve is closed to respond.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are given by way of illustration of the principles of the present invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, and such changes and modifications are within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (3)
1. The electromagnetic valve measurement and control system for spaceflight is characterized in that: the thruster and the electromagnetic valve are assembled into an engine, the engine is fixed on a test bed, the pressure sensor is connected to the thruster, the vibration sensor is fixed on an engine support, the temperature sensor is pasted on the thruster, a control cable of the pressure sensor, the vibration sensor and the temperature sensor is connected to the electromagnetic valve measurement and control system, the electromagnetic valve measurement and control system is in signal connection with a computer, the electromagnetic valve measurement and control system adopts a NIUSB6210 controller, the NIUSB6210 controller collects field signals and stores the signals, and outputs control signals.
2. The electromagnetic valve measurement and control system for aerospace according to claim 1, wherein: the control signal output by the NI USB6210 controller is output to the optical coupler isolator in a digital quantity mode, the control signal is amplified by the optical coupler isolator and then output to the electromagnetic valve interface, the electromagnetic valve interface outputs a current signal to the current sensor, and the current sensor outputs a 0-10V voltage signal to the analog quantity input end of the NI USB6210 controller.
3. The electromagnetic valve measurement and control system for aerospace according to claim 1, wherein: the power supply of the electromagnetic valve measurement and control system is divided into two paths, one path of the power supply introduces a bipolar linear power supply and a unipolar switching power supply to supply power for the current sensor and the pressure sensor; and the other path is externally connected with a power supply through a panel driving interface to supply power to the valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210041356.4A CN114527689A (en) | 2022-01-14 | 2022-01-14 | Electromagnetic valve measurement and control system for spaceflight |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210041356.4A CN114527689A (en) | 2022-01-14 | 2022-01-14 | Electromagnetic valve measurement and control system for spaceflight |
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| CN114527689A true CN114527689A (en) | 2022-05-24 |
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| CN202210041356.4A Pending CN114527689A (en) | 2022-01-14 | 2022-01-14 | Electromagnetic valve measurement and control system for spaceflight |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116930668A (en) * | 2023-09-15 | 2023-10-24 | 国科大杭州高等研究院 | Detection system and operation method for measuring response time of electric thruster |
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2022
- 2022-01-14 CN CN202210041356.4A patent/CN114527689A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116930668A (en) * | 2023-09-15 | 2023-10-24 | 国科大杭州高等研究院 | Detection system and operation method for measuring response time of electric thruster |
| CN116930668B (en) * | 2023-09-15 | 2023-12-05 | 国科大杭州高等研究院 | Detection system and operation method for measuring response time of electric thruster |
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