CN116047957A - Fuel control system - Google Patents
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- CN116047957A CN116047957A CN202211684492.1A CN202211684492A CN116047957A CN 116047957 A CN116047957 A CN 116047957A CN 202211684492 A CN202211684492 A CN 202211684492A CN 116047957 A CN116047957 A CN 116047957A
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- 239000000446 fuel Substances 0.000 title claims abstract description 123
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 30
- 238000012545 processing Methods 0.000 claims abstract description 21
- 238000012937 correction Methods 0.000 claims abstract description 19
- 230000005540 biological transmission Effects 0.000 claims abstract description 13
- 238000001914 filtration Methods 0.000 claims abstract description 13
- 238000000034 method Methods 0.000 claims description 14
- 230000008569 process Effects 0.000 claims description 13
- 238000012544 monitoring process Methods 0.000 abstract description 11
- 239000002828 fuel tank Substances 0.000 abstract description 8
- 239000003921 oil Substances 0.000 description 85
- 238000004364 calculation method Methods 0.000 description 5
- 238000004891 communication Methods 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 230000001960 triggered effect Effects 0.000 description 2
- 230000005587 bubbling Effects 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000012163 sequencing technique Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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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
- G05B19/0423—Input/output
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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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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a fuel control system, comprising: the data acquisition unit is used for acquiring analog quantity data and digital quantity data; the data processing unit is used for performing data processing after the data acquisition unit finishes data acquisition, including filtering, resolving, recursion and correction processing; the data transmission unit is used for communicating with the flight control computer, and comprises uploading analog quantity data, digital quantity data and a specific identifier to the flight control computer and receiving a downlink instruction of the flight control computer; and the oil pump control unit analyzes after the data transmission unit receives the control instruction issued by the flight control computer and is used for controlling the main oil pump and the auxiliary oil pump. The system of the invention realizes the power supply control and the power supply current monitoring of the main fuel pump and the auxiliary fuel pump by monitoring parameters such as fuel temperature, main and auxiliary fuel quantity, main and auxiliary fuel pump current, fuel pressure, fuel tank pressure and the like, calculating the fuel quantity and receiving a low fuel quantity alarm signal when the fuel quantity is low.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle flight control, in particular to a fuel control system.
Background
When the unmanned aerial vehicle is in flight operation, a special fuel control system is required to be designed because of unmanned, and the special fuel control system is used for monitoring parameters such as fuel temperature, fuel quantity, main and auxiliary oil pump current, fuel pressure, oil tank pressure and the like in real time, calculating the fuel quantity, receiving a low-fuel quantity alarm signal when the fuel quantity is low, realizing power supply control and power supply current monitoring of the main and auxiliary fuel pumps, and ensuring the flight safety of the unmanned aerial vehicle.
The information disclosed in the background section of the invention is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.
Disclosure of Invention
The invention provides a fuel control system, which belongs to embedded software, wherein a main control board is based on a TMS320F28335 processor and has a fuel system state monitoring function, and the functions of uploading fuel system state information, receiving and analyzing control instructions of a flight control computer, controlling the on and off of a main fuel pump and an auxiliary fuel pump and alarming low fuel level are included.
The present invention provides a fuel control system, comprising:
the data acquisition unit is used for acquiring analog quantity data and digital quantity data;
the data processing unit is used for performing data processing after the data acquisition unit finishes data acquisition, including filtering, resolving, recursion and correction processing;
the data transmission unit is used for communicating with the flight control computer, and comprises uploading analog quantity data, digital quantity data and a specific identifier to the flight control computer and receiving a downlink instruction of the flight control computer;
and the oil pump control unit analyzes after the data transmission unit receives the control instruction issued by the flight control computer and is used for controlling the main oil pump and the auxiliary oil pump.
Further, the system comprises an initialization unit, wherein the initialization unit performs system initialization after the system is powered on, and the system clock initialization, interrupt initialization, SCI initialization, timer initialization, SPI initialization and GPIO initialization are included.
Further, the initialization unit is used for initializing the initialization setting related to the DSP, initializing the status zone bit of each other unit and other data and completing serial port protocol setting.
Further, the self-checking device also comprises a self-checking unit, wherein the self-checking unit judges whether self-checking is needed or not through the status flag bit, if so, the self-checking unit judges the serial port data flag bit, then executes a corresponding self-checking program and uploads data.
Further, the analog quantity data comprises a main oil pump current, an auxiliary oil pump current, a fuel temperature, a fuel pressure, a main oil tank oil quantity, an auxiliary oil tank oil quantity and an oil tank pressure;
the digital data comprise a main oil pump state, an auxiliary oil pump state and a low oil level alarm state, and the low oil level alarm state corresponds to the main oil tank.
Further, the filtering process needs to perform digital filtering on the acquired analog data to improve accuracy of the data.
Further, the resolving process needs to resolve the acquired analog quantity data to obtain an actual characterization value corresponding to each analog voltage value.
Further, the recursion process requires recursion of the acquired analog and digital data;
the correction processing needs to perform corresponding correction on the analog data after recursion so as to meet corresponding data resolution requirements.
Further, the oil pump control unit completes switching of the working states of the main oil pump and the auxiliary oil pump according to the four states of the main oil pump working, the auxiliary oil pump working, the double oil pump working and the double oil pump stopping working.
Further, the data format transmitted by the data transmission unit is 8-bit data, one-bit start bit, one-bit stop bit, no parity check, and byte exclusive or check is adopted for the checksum; when multi-byte data is transmitted, the low byte is before and the high byte is after; the unsigned data is represented by an original code and the signed data is processed in a data shifted form.
The fuel control system receives a flight control computer control instruction through a data communication serial port, realizes the on-off control of the main and auxiliary oil pumps, and simultaneously acquires sensor data such as fuel temperature, fuel pressure, fuel tank pressure, main and auxiliary oil pump current, main and auxiliary oil tank oil mass and the like in the fuel system; collecting a fuel low oil level alarm signal; and uploading the acquired data to the flight control computer through the communication serial port.
The method and apparatus of the present invention have other features and advantages which will be apparent from or are set forth in detail in the accompanying drawings and the following detailed description, which are incorporated herein, and which together serve to explain certain principles of the present invention.
Drawings
The foregoing and other objects, features and advantages of the invention will be apparent from the following more particular descriptions of exemplary embodiments of the invention as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the invention.
FIG. 1 illustrates an interface diagram of a fuel control system according to an embodiment of the present invention.
FIG. 2 illustrates a data acquisition profile of a fuel control system AD7606, according to an embodiment of the invention.
Fig. 3 shows a schematic diagram of a fuel control system according to an embodiment of the invention.
Fig. 4 shows a self-test flow chart of a fuel control system according to an embodiment of the invention.
Fig. 5 shows an AD interrupt flow chart of the fuel control system according to an embodiment of the invention.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the preferred embodiments of the present invention are described below, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein.
The invention discloses a fuel control system, which is used for realizing power supply control and power supply current monitoring of a main fuel pump and a secondary fuel pump by monitoring parameters such as fuel temperature, main fuel and secondary fuel quantity, main fuel and secondary fuel pump current, fuel pressure, fuel tank pressure and the like, calculating the fuel quantity and receiving a low fuel quantity alarm signal when the fuel quantity is low. After the fuel control system operates, the initialization and power-on self-checking tasks are firstly carried out, and under the normal condition of self-checking, corresponding monitoring and measuring information is sent to the flight control computer.
Specifically, the invention provides a fuel control system, comprising:
the data acquisition unit is used for acquiring analog quantity data and digital quantity data;
the data processing unit is used for performing data processing after the data acquisition unit finishes data acquisition, including filtering, resolving, recursion and correction processing;
the data transmission unit is used for communicating with the flight control computer, and comprises uploading analog quantity data, digital quantity data and a specific identifier to the flight control computer and receiving a downlink instruction of the flight control computer;
and the oil pump control unit analyzes after the data transmission unit receives the control instruction issued by the flight control computer and is used for controlling the main oil pump and the auxiliary oil pump.
Specifically, the system of the fuel control system comprises units such as initialization, self-checking, data acquisition, data processing, oil pump control, data transmission and the like.
The initialization unit executes initialization after the system is powered on, including tasks such as system clock initialization, interrupt initialization, SCI initialization, timer initialization, SPI initialization, GPIO initialization and the like, and the main functional requirements are as follows:
a) Performing initialization settings related to the DSP, such as system clock, timer, AD acquisition period, watchdog, SCI, SPI, etc.;
b) Initializing the status zone bit and other data of other modules;
c) Serial protocol settings such as baud rate, start bit, data bit, parity, etc. are completed.
The self-checking unit judges whether self-checking is needed or not through a status flag bit (FCUStatus), if so, the self-checking unit executes a corresponding self-checking program after judging a serial port data flag bit (FCUUArtStatus) and uploads data. Otherwise, the normal working mode is entered.
And after the power-on initialization and self-checking functions are completed, the data acquisition unit performs the tasks of acquiring analog quantity and digital quantity data. The analog data acquisition comprises 7 channels in total of main and auxiliary oil pump current, fuel temperature, fuel pressure, main and auxiliary oil quantity and oil tank pressure, wherein the main and auxiliary oil pump current acquisition is two channels corresponding to the main oil pump and the auxiliary oil pump respectively, and the main and auxiliary oil quantity acquisition is two channels corresponding to the main oil tank and the auxiliary oil tank respectively. The digital quantity collection comprises a main oil pump and auxiliary oil pump state collection and a low oil level alarm state collection, wherein the main oil pump and auxiliary oil pump state collection is two channels, respectively corresponds to the main oil pump and the auxiliary oil pump, and the low oil level alarm state collection is one channel and corresponds to the main oil tank.
The data processing unit is executed after the data acquisition function is completed, and the data processing function is divided into a filtering function, a resolving function, a recursion function and a correction process.
Specifically, the filtering process needs to digitally filter the collected analog data, such as the current of the main and auxiliary oil pumps, the temperature of the fuel, the pressure of the fuel, the main and auxiliary oil quantities and the pressure of the oil tank, so as to improve the accuracy of the data.
The calculation process needs to calculate analog data collected by the fuel control system, such as main and auxiliary fuel pump current, fuel temperature, fuel pressure, main and auxiliary fuel amount and fuel tank pressure 7 channel data, so as to obtain an actual representation value corresponding to each analog voltage value.
The recursion processing needs to recursion 7-channel analog quantity data and 3-channel digital quantity data acquired by the fuel controller so as to ensure the smoothness of the corresponding analog quantity data and the accuracy of the digital quantity data.
The correction process needs to make corresponding corrections to the analog data after recursion to achieve the corresponding data resolution requirements.
The oil pump control unit analyzes after the fuel control system receives the control instruction issued by the flight control computer, and controls the main oil pump and the auxiliary oil pump after the control instruction is completed, wherein the four states of main oil pump operation, auxiliary oil pump operation, double oil pump operation and double oil pump stop operation are included. The fuel control system needs to complete the switching of the working states of the main oil pump and the auxiliary oil pump according to the four states, and perfects the control strategy according to the requirement of hardware error prevention control.
The data transmission unit is used for communicating the fuel control system with the flight control computer through one path of RS422 and comprises two paths of communication of uploading and downloading. The fuel control system frames the analog quantity data, the digital quantity data and the specific mark and uploads the frames to the flight control computer; after receiving the downlink instruction of the flight control computer, the fuel control system finishes the work of distinguishing the identification code, receiving the command class word, receiving the command word and comparing the checksum.
Specifically, the data format is 8-bit data, one-bit start bit, one-bit stop bit, no parity check, and byte exclusive-or check (including sync byte, ID frame identification frame, etc. in calculation) is adopted for the checksum, and the baud rate is 19.2Kbps. When multi-byte data is transmitted, the appointed low byte is before and the appointed high byte is after; the unsigned data is represented by an original code and the signed data is processed in a data shifted form.
The invention is further described below with reference to the drawings and specific examples, which are not intended to be limiting. It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other.
Referring to fig. 1-5, the present embodiment provides a fuel control system, where a system main control board includes a power-on initialization function, a self-checking function, a data acquisition function, a filtering function, a resolving function, a recursion function, a correction function, an oil pump control function, and an RS422 function based on TMS320F 28335.
The fuel control system can collect fuel temperature, fuel pressure, fuel tank pressure, main and auxiliary fuel oil quantity, main and auxiliary oil pump current 7-channel analog quantity data, low oil quantity alarm signal and main and auxiliary oil pump state 3-channel discrete quantity data.
The fuel control system is provided with an RS422 interface, can perform data interaction with the flight control computer, adopts a communication protocol of 11 bytes in the downlink and 39 bytes in the uplink, and has a communication baud rate of 19200bps.
The fuel control system is provided with a main and auxiliary oil pump current acquisition interface which can acquire main and auxiliary oil pump current data, wherein the main and auxiliary oil pump current data are positioned in the 0 th channel and the 1 st channel data of the AD acquisition 8 channels, and the data are converted into uploading values after resolving, filtering, recursion and correction.
The fuel control system is provided with a fuel temperature interface, fuel temperature data are located in the 7 th channel data acquired by the AD, acquired voltage values are converted into resistance values after temperature acquisition is performed through a temperature sensor, and then the resistance values are converted into temperature values through a corresponding calculation formula, and the temperature values are converted into uploading values after recursion and correction.
The fuel control system is provided with a fuel quantity and low-oil-level alarm interface, fuel quantity data are located in a 2 nd channel and a 4 th channel of data acquired by the AD, and 1# and 2# oil level signals (0-5V analog quantity) are output through the oil level measuring unit and converted into uploading values after resolving, recursion and correction. The oil level measuring unit outputs a low oil level warning signal (discrete quantity).
The fuel control system is provided with a fuel pressure interface and can collect fuel pressure data. The fuel pressure data is located in the 6 th channel data acquired by the AD, the measurement of the pressure is realized through a fuel pressure sensor, and the fuel pressure data is converted into an uploading value after calculation, recursion and correction.
The fuel control system is provided with a fuel tank pressure interface and can collect fuel tank pressure data. The oil tank pressure data is located in the 5 th channel data acquired by the AD, pressure output is achieved through the oil tank pressure sensor, and the data is converted into an uploading value after resolving, recursion and correction.
The fuel control system is provided with a main and auxiliary oil pump state and a control interface, wherein the main and auxiliary oil pump state is discrete quantity, the main and auxiliary fuel pump state is acquired through GPIO51 and GPIO55 in TMS320F28335, and the final signal is judged according to a digital quantity recursion algorithm.
The fuel control system is provided with a firmware interface, and fuel control software is solidified into Flash of TMS320F28335 through a Texas Instruments XDS v3 USB simulator and JTAG interface.
Specifically, the power-on initialization function is executed after the system is powered on, and the main frequency of the system clock is set to be 60MHz; setting the interrupt period of a Timer Timer0 to be 1ms; setting 2ms to trigger AD acquisition once, namely triggering AD interruption once every 2 Timer0 interruption; setting the data update rate of 2Hz, which is to upload data to the flight control computer every 500 ms; the watchdog restarted counting every 50 ms; initializing relevant status flag bit data and other data; and finishing serial port protocol setting, wherein the baud rate is set to 19200bps, 1-bit start bit, 8-bit data bit and no parity check bit.
After the initialization is finished, as shown in fig. 4, the fuel controller software judges whether self-checking is needed through a status flag bit (fcustattus), if so (fcustattus= 0), then after judging the serial port data flag bit (FCUUartStatus), executes a corresponding self-checking program, uploads self-checking information (fcuuartstatus= 0), otherwise, enters a normal working mode.
After the system is powered on and initialized, as shown in fig. 2 and 5, when the AD interrupt is triggered, the analog Data Acquisition System (DAS) synchronously samples analog data through an AD7606 16 bit 8 channel, receives data by using an SPI FIFO of TMS320F28335, and converts the data into a voltage value when the data is written into a corresponding data queue (circulation queue) AD1 ScanQuue, thus completing the data acquisition work of 7 channels. The corresponding amount of 7-channel data acquisition is: primary and secondary fuel pump current, fuel gauge 2, fuel gauge 1, tank pressure, fuel pressure, and fuel temperature.
The filtering function is executed after the data acquisition is finished, and is mainly used for processing the acquired 7-channel analog quantity data. Specifically, 50 groups of data are dequeued from each channel in an acquired AD1ScanQueue queue, then AD1MiddleData is enqueued, 50 groups of data of each enqueued channel are subjected to bubbling sequencing, average value Average is calculated on 12 th-37 th groups of data (0 th-11 th groups and 38 th-49 th groups of data are removed, burr data are filtered), and finally Average is enqueued in an AD1RealQueue circular queue.
After the AD acquires 7-channel analog quantity data, the resolving function needs to convert the corresponding voltage value into an actual representation value of the corresponding quantity, and the function is realized according to a resolving formula of the corresponding quantity, for example, in the fuel oil quantity resolving process, the acquired voltage value needs to be converted into a represented fuel oil quantity value according to the fuel oil quantity resolving formula. The remaining analog data calculation methods are similar and will not be described in detail herein.
The recursion function is to process the acquired 8-channel analog quantity data and 3-channel digital quantity data. For analog data, after Average enqueues AD1RealQueue, average is calculated again every 6 Average to obtain value return value, so that the smoothness of the data can be ensured. And judging the acquired Digital quantity signal (1 or 0), wherein the Digital quantity processing queue is FuelDataQuue_digital, the length of the circular queue is 6, judging 1 and 0 for every 5 groups of data, adding 1 to the total value Cnt if the value is 1, subtracting 1 from the total value Cnt if the value is 0, and finally judging the final signal recursion result by judging whether the value of Cnt is greater than or equal to 1.
The correction function is to process the analog data finally, which is realized by AD1 DataCalculation_K8 and AD1 DataCalculation_B8, the AD1 DataCalculation_K8 carries out corresponding coefficient correction to the 8 channel analog data before uploading, the AD1 DataCalculation_B8 carries out compensation to the 8 channel analog data before uploading, which ensures the accuracy of the final uploading data and reaches the corresponding data resolution requirement.
After analyzing the downlink command sent by the flight control computer, the oil pump control function analyzes the 8 th-10 th byte of the downlink data frame, the command belongs to the oil pump control command, the 8 th, 9 th and 10 th byte commands are identical, 0xB1 represents the operation of the main oil pump, 0xB2 represents the operation of the auxiliary oil pump, 0xB3 represents the operation of the double oil pump, and 0xB4 represents the stop of the double oil pump.
After the data transmission function completes the data acquisition and the processing, the data packet is framed through the SCI and then uploaded. Wherein GPIO63 is set to SCI transmit and GPIO62 is set to SCI receive. After the serial port of the fuel control system is interrupted and triggered, the downlink instruction issued by the flight control computer is received, whether the frame is the frame head or not is firstly judged, namely whether the first byte is 0xEB is firstly judged, if the judging result is correct, whether the next byte is 0x90 is judged, if the judging result is correct, the subsequent data is read in, and after 11 characters are received, the data is written into the receiveData 11 by taking the length of the 11 frames as the judging condition.
The system of the invention realizes the power supply control and the power supply current monitoring of the main fuel pump and the auxiliary fuel pump by monitoring parameters such as fuel temperature, main and auxiliary fuel quantity, main and auxiliary fuel pump current, fuel pressure, fuel tank pressure and the like, calculating the fuel quantity and receiving a low fuel quantity alarm signal when the fuel quantity is low. After the fuel control system operates, the initialization and power-on self-checking tasks are firstly carried out, and under the normal condition of self-checking, corresponding monitoring and measuring information is sent to the flight control computer.
The foregoing description of embodiments of the invention has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.
Claims (10)
1. A fuel control system, comprising:
the data acquisition unit is used for acquiring analog quantity data and digital quantity data;
the data processing unit is used for performing data processing after the data acquisition unit finishes data acquisition, including filtering, resolving, recursion and correction processing;
the data transmission unit is used for communicating with the flight control computer, and comprises uploading analog quantity data, digital quantity data and a specific identifier to the flight control computer and receiving a downlink instruction of the flight control computer;
and the oil pump control unit analyzes after the data transmission unit receives the control instruction issued by the flight control computer and is used for controlling the main oil pump and the auxiliary oil pump.
2. The fuel control system according to claim 1, further comprising an initialization unit that performs system initialization after system power-up, including system clock initialization, interrupt initialization, SCI initialization, timer initialization, SPI initialization, GPIO initialization.
3. The fuel control system according to claim 2, wherein the initialization unit is configured to perform initialization setting related to the DSP, initialization of status flags of the remaining units and other data, and completion of serial port protocol setting.
4. The fuel control system according to claim 1, further comprising a self-checking unit, wherein the self-checking unit determines whether self-checking is required according to the status flag bit, and if self-checking is required, executes a corresponding self-checking program after determining the serial port data flag bit, and uploads data.
5. The fuel control system of claim 1, wherein the analog data includes a main oil pump current, a sub oil pump current, a fuel temperature, a fuel pressure, a main tank oil amount, a sub tank oil amount, a tank pressure;
the digital data comprise a main oil pump state, an auxiliary oil pump state and a low oil level alarm state, and the low oil level alarm state corresponds to the main oil tank.
6. The fuel control system of claim 5, wherein the filtering process requires digital filtering of the acquired analog data to improve data accuracy.
7. The fuel control system of claim 5, wherein the resolving process is configured to resolve the collected analog data to obtain an actual representation value corresponding to each analog voltage value.
8. The fuel control system of claim 5, wherein the recursive process entails recursively collecting analog data and digital data;
the correction processing needs to perform corresponding correction on the analog data after recursion so as to meet corresponding data resolution requirements.
9. The fuel control system according to claim 1, wherein the oil pump control unit completes switching of the operating states of the main oil pump and the sub oil pump in accordance with four states of operation of the main oil pump, operation of the sub oil pump, operation of the double oil pump, and stop of operation of the double oil pump.
10. The fuel control system according to claim 1, wherein the data format transmitted by the data transmission unit is 8-bit data, one-bit start bit, one-bit stop bit, no parity, and byte exclusive or check is used for the checksum; when multi-byte data is transmitted, the low byte is before and the high byte is after; the unsigned data is represented by an original code and the signed data is processed in a data shifted form.
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| CN202211684492.1A CN116047957A (en) | 2022-12-27 | 2022-12-27 | Fuel control system |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030040897A1 (en) * | 1996-04-03 | 2003-02-27 | Murphy Thomas Andrew | Man machine interface for power management control systems |
| WO2018113165A1 (en) * | 2016-12-21 | 2018-06-28 | 国网电力科学研究院 | Configurable device for monitoring vibration and swing states of hydraulic turbine set, and data acquisition method |
| CN207881745U (en) * | 2017-11-30 | 2018-09-18 | 中国科学院工程热物理研究所 | Unmanned plane sensor parameters acquisition system |
| CN208476347U (en) * | 2018-06-26 | 2019-02-05 | 中国航天空气动力技术研究院 | Integrated aero-engine fuel measurement monitoring device |
| CN114370361A (en) * | 2021-11-26 | 2022-04-19 | 中国航天空气动力技术研究院 | High prototype unmanned aerial vehicle's fuel control system and high prototype unmanned aerial vehicle |
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2022
- 2022-12-27 CN CN202211684492.1A patent/CN116047957A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030040897A1 (en) * | 1996-04-03 | 2003-02-27 | Murphy Thomas Andrew | Man machine interface for power management control systems |
| WO2018113165A1 (en) * | 2016-12-21 | 2018-06-28 | 国网电力科学研究院 | Configurable device for monitoring vibration and swing states of hydraulic turbine set, and data acquisition method |
| CN207881745U (en) * | 2017-11-30 | 2018-09-18 | 中国科学院工程热物理研究所 | Unmanned plane sensor parameters acquisition system |
| CN208476347U (en) * | 2018-06-26 | 2019-02-05 | 中国航天空气动力技术研究院 | Integrated aero-engine fuel measurement monitoring device |
| CN114370361A (en) * | 2021-11-26 | 2022-04-19 | 中国航天空气动力技术研究院 | High prototype unmanned aerial vehicle's fuel control system and high prototype unmanned aerial vehicle |
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