Electronic resume system for aircraft

Abstract

The invention provides an electronic resume system for an aircraft. The electronic resume system comprises an acquisition device, a communication module and a data management system, the acquisition device is mounted in the aircraft and comprises a temperature, humidity and pressure sensor, an electric connector, a shell and a cover body; the communication module is mounted outside the aircraft and comprises a box body, a box cover, a storage chip, a communication unit, a printed board, a battery and a connector; the data management system comprises an upper computer, data management software and a database. Temperature, humidity and pressure sensors are integrated, so that internal environment parameters of the aircraft can be monitored; by configuring the low-power-consumption mode of the main control chip, the standby time is long; through a wireless communication technology, parameter changes of a plurality of aircrafts can be remotely monitored in real time or internal environment parameters periodically and autonomously collected in a storage chip can be read; according to the system, the management efficiency of the aircraft is greatly improved, and the maintenance cost is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of equipment information management, and in particular relates to an electronic resume system for aircraft. Background Art

[0002] At present, with the development of science and technology, users have higher and higher requirements for aircraft. It is necessary to check the internal environmental parameters of the aircraft during ground storage, including temperature, humidity, and pressure, in real time, so as to promptly discover faults that may be caused by changes in the internal environmental parameters of the aircraft. At the same time, the power-on time and environmental parameter information must be stored, and the stored data can be checked and read back at any time.

[0003] The Chinese patent with patent number CN115481185A discloses a non-contact aircraft electronic resume realization device, which includes an RFID electronic tag, an RFID reader / writer, an information processing terminal and an aircraft control system; the RFID electronic tag is set in a test port cover on the surface of the aircraft, the RFID electronic tag exchanges information with the RFID reader / writer through an air interface, the RFID electronic tag exchanges information with the aircraft control system through an IIC bus interface, and the RFID reader / writer exchanges information with the information processing terminal through a network; the test port cover is conformally integrated with the aircraft body and is provided with a wave-transmitting area. The patent uses RFID electronic tags to realize wireless communication technology, but this method has the disadvantages of short communication distance and low security.

[0004] The Chinese patent with patent number CN117313780A discloses a method and device for recording electronic resumes of aircraft test equipment. The patent includes setting a Flash chip, a CH340 chip and an 80C51 chip in the electronic resume device, and using a USB interface reinforced by an aviation plug to design the electronic resume device. The electronic resume device is installed on the test equipment computer combination, and the computer combination terminal or the test system uses a CH340 chip for USB connection; the electronic resume device communicates with the CH340 chip through the 80C51 chip and the data is encrypted, decrypted, read and written into the Flash chip according to the terminal command of the computer combination; the upper computer software is used to provide a human-computer interaction interface, communicate with the lower computer of the electronic resume device, and realize import and export functions. This patent can only monitor the relevant parameters of the aircraft during the aircraft test process, and cannot meet the monitoring needs during the aircraft transportation and storage process.

[0005] Therefore, a technical solution is needed to solve the problem that the electronic record communication distance of the aircraft is short and can be monitored for a long time. Summary of the invention

[0006] To solve the above problems, the technical solution of the present invention is as follows:

[0007] An electronic resume system for aircraft, characterized in that it includes: a collection device, a communication module and a data management system;

[0008] Collection device: installed inside the aircraft, including temperature, humidity and pressure sensors, electrical connectors, shells and cover bodies. The temperature, humidity and pressure sensors and electrical connectors are installed inside the shells. The cover body is installed on the shells. There are small holes on the cover body to facilitate the temperature, humidity and pressure sensors to collect environmental parameters inside the equipment. The overall dimensions of the components installed in the aircraft are φ52mm×60mm;

[0009] Communication module: installed on the outside of the aircraft, including box body, box cover, storage chip, communication unit, printed circuit board, battery and connector; the box cover is installed on the top surface of the box body, and the battery, printed circuit board, storage chip and communication unit are fixed inside the box body. The communication unit is used to realize communication with the data management system; the connector is inserted from the bottom of the box body to connect the electrical connector of the acquisition device; in order to facilitate the transmission of wireless communication signals, the box cover material is made of wave-transmitting material epoxy resin laminate EP GC 201, and the maximum size of the components outside the box is 135mm×115mm×100mm;

[0010] The data management system includes: a host computer, data management software and a database; the data management software is written in Labview language and integrated with the database; the host computer runs the data management software and database and receives information from the communication module; the main functions of the data management software include communication, parameter display, data storage, historical data query, maintenance reminder and downloading of power-on times.

[0011] The temperature, humidity and pressure sensor in the acquisition device adopts a PCB type temperature, humidity and pressure sensor, which can output the collected temperature, humidity and pressure environmental parameter data according to the Modbus-RTU protocol. Its performance indicators are as follows:

[0012] 1) Temperature

[0013] Measuring range: -40~100℃;

[0014] Measurement accuracy: ±0.3℃;

[0015] Data processing and display resolution: 0.1℃;

[0016] 2) Humidity

[0017] Measuring range: 0%RH~100%RH;

[0018] Measurement accuracy: ±2%RH;

[0019] Data processing and display resolution: 0.1%RH;

[0020] 3) Pressure

[0021] Measuring range: +20~+175kPa;

[0022] Measurement accuracy: ±1.5kPa;

[0023] Data processing and display resolution: 0.01kPa.

[0024] The printed circuit board in the communication module includes a main control circuit, a communication circuit and a storage circuit;

[0025] The main control circuit includes a main control chip, the embedded software is burned into the main control chip, and the main control chip uses a 32-bit microcontroller STM32F103VB;

[0026] The communication circuit is connected to the communication unit;

[0027] The storage circuit is connected to the storage chip;

[0028] Furthermore, the main control chip is used for:

[0029] Monitor the 27V input power supply voltage. Use the 12-bit AD acquisition port of the microcontroller to collect the input power supply voltage value to monitor the 27V input power supply voltage. The voltage signal range is 0 to 32V.

[0030] Collect temperature, humidity and pressure from temperature, humidity and pressure sensors;

[0031] The collected temperature, humidity, pressure data, and the number of power-on times sent by the host computer are stored through the IIC communication protocol;

[0032] Realize wireless communication: receive host computer instructions through wireless communication, parse and execute instructions, and reply to the host computer; send the collected information to the host computer through wireless communication.

[0033] The communication unit uses the ATK-LORA wireless serial port submodule for communication. The submodule is based on the SX1278 radio frequency chip, with a maximum communication distance of 3000m and an operating frequency band of 410-441Mhz.

[0034] The storage chip uses a 16M external Flash storage chip to store environmental parameter information, which can store more than 10,000 pieces of environmental parameter information.

[0035] The data storage function of the data management software includes: storing the monitored real-time data in the database and querying the data stored in the database by time.

[0036] When there is no external power supply, the acquisition device and communication module are powered by the internal lithium battery. When there is external power supply, the battery power supply is disconnected.

[0037] The main control chip STM32F103VB supports the configuration of low power mode. The system is usually in low power mode and automatically wakes up at specified intervals to collect and store environmental parameters. During low power mode, if the host computer communication wake-up command is received, the original recorded data will be uploaded to the host computer management system immediately, and real-time data collection and transmission will be performed. The ATK-LORA wireless serial communication submodule used has a power saving mode, and the power consumption is as low as 2.3μA when in sleep mode.

[0038] The maintenance reminder function is implemented as follows: the input voltage of the electronic resume system is monitored to identify the battery power; the voltage is input into the isolation transmitter for isolation transformation, converted into a 0-5V voltage signal, and sent to the ADC port of the microcontroller for collection; the data management software interprets the monitored data and issues equipment maintenance reminders when it exceeds the specified threshold.

[0039] The present invention has the following beneficial effects:

[0040] 1) It has real-time monitoring function and integrates temperature, humidity and pressure sensors to monitor changes in three environmental parameters: temperature, humidity and pressure in the aircraft;

[0041] 2) It has data recording function, and can record and store information such as environmental parameters, cumulative power-on times and power-on time. The storage capacity of the hardware equipment is not less than 10,000 records. The upper computer management software integrates the database and can store and read back the received data;

[0042] 3) It has long-lasting power supply capability and relies on lithium batteries for power supply. It is usually in low-power mode and automatically wakes up periodically to collect and store environmental parameters. After receiving the communication wake-up command from the host computer, it establishes communication with the host computer;

[0043] 4) It has remote access function and can transmit data to the outside through wireless transmission according to the needs of the host computer. The communication distance is greater than 1000 meters;

[0044] 5) It has a maintenance reminder function, monitors the input voltage to identify the battery power, and reminds you to charge when the battery voltage is lower than 16V. It also judges the environmental parameters inside the cylinder and reminds you when there is an abnormality.

[0045] 6) It has the function of historical data query, and the upper computer management software can query the stored historical data. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 A diagram of the system composition provided by an embodiment of the present invention;

[0047] Figure 2 A structural diagram of a collection device provided in an embodiment of the present invention;

[0048] Figure 3 A structural diagram of a communication module provided in an embodiment of the present invention;

[0049] Figure 4 A functional structure diagram of the data management software provided by an embodiment of the present invention;

[0050] In the figure: 1-acquisition device; 2-communication module; 3-data management system; 4-temperature, humidity and pressure sensor; 5-electrical connector; 6-housing; 7-cover; 8-box body; 9-box cover; 10-storage chip; 11-communication unit; 12-printed circuit board; 13-battery; 14-connector. DETAILED DESCRIPTION

[0051] The specific implementation modes of the present invention are described in detail below with reference to the accompanying drawings.

[0052] An electronic resume system for aircraft, characterized in that it includes: a collection device 1, a communication module 2 and a data management system 3; the system composition can be found in Figure 1 .

[0053] Collection device 1: installed inside the aircraft, including temperature, humidity and pressure sensor 4, electrical connector 5, shell 6 and cover 7. The temperature, humidity and pressure sensor 4 and electrical connector 5 are installed in the shell 6. The cover 7 is installed on the shell 6. There are small holes on the cover 7 to facilitate the temperature, humidity and pressure sensor 4 to collect environmental parameters in the equipment. The size of the component installed in the aircraft is φ52mm×60mm. For the structure of the collection device 1, please refer to Figure 2 .

[0054] The temperature, humidity and pressure sensor 4 in the acquisition device 1 is a PCB temperature, humidity and pressure sensor 4, which can output the collected temperature, humidity and pressure environmental parameter data according to the Modbus-RTU protocol. Its performance indicators are as follows:

[0055] 1) Temperature

[0056] Measuring range: -40~100℃;

[0057] Measurement accuracy: ±0.3℃;

[0058] Data processing and display resolution: 0.1℃;

[0059] 2) Humidity

[0060] Measuring range: 0%RH~100%RH;

[0061] Measurement accuracy: ±2%RH;

[0062] Data processing and display resolution: 0.1%RH;

[0063] 3) Pressure

[0064] Measuring range: +20~+175kPa;

[0065] Measurement accuracy: ±1.5kPa;

[0066] Data processing and display resolution: 0.01kPa.

[0067] For the structure of communication module 2, please refer to Figure 3 , Communication module 2: installed outside the aircraft, including box body 8, box cover 9, storage chip 10, communication unit 11, printed circuit board 12, battery 13 and connector 14; box cover 9 is installed on the top surface of box body 8, battery 13, printed circuit board 12, storage chip 10 and communication unit 11 are fixedly installed inside box body 8, and communication unit 11 is used to realize communication with data management system 3; connector 14 passes through the bottom of box body 8 to connect the electrical connector 5 of acquisition device 1; in order to facilitate the transmission of wireless communication signals, the material of box cover 9 is made of wave-transmitting material epoxy resin laminate EP GC 201, and the maximum size of the outer box component is 135mm×115mm×100mm;

[0068] The printed circuit board 12 includes a main control circuit, a communication circuit and a storage circuit;

[0069] The main control circuit includes a main control chip, the embedded software is burned into the main control chip, and the main control chip uses a 32-bit microcontroller STM32F103VB;

[0070] The communication circuit is connected to the communication unit 11;

[0071] The storage circuit is connected to the storage chip 10;

[0072] Furthermore, the main control chip is used for:

[0073] Monitor the 27V input power supply voltage. Use the 12-bit AD acquisition port of the microcontroller to collect the input power supply voltage value to monitor the 27V input power supply voltage. The voltage signal range is 0 to 32V.

[0074] Collect the temperature, humidity and pressure of the temperature, humidity and pressure sensor 4;

[0075] The collected temperature, humidity, pressure data, and the number of power-on times sent by the host computer are stored through the IIC communication protocol;

[0076] Realize wireless communication: receive host computer instructions through wireless communication, parse and execute instructions, and reply to the host computer; send the collected information to the host computer through wireless communication.

[0077] The communication unit 11 uses the ATK-LORA wireless serial port submodule for communication. The submodule is based on the SX1278 radio frequency chip, has a maximum communication distance of 3000m, and an operating frequency band of 410-441Mhz.

[0078] The storage chip 10 uses a 16M external Flash storage chip 10 for storing environmental parameter information and can store more than 10,000 pieces of environmental parameter information.

[0079] The data management system 3 includes: a host computer, data management software and a database; the data management software is written in Labview language and integrated with the database; the host computer runs the data management software and database and receives information from the communication module 2; the main functions of the data management software include communication, parameter display, data storage, historical data query, maintenance reminder and downloading of power-on times. Please refer to the functional structure of the data management software Figure 4 .

[0080] The data storage function includes: storing the monitored real-time data in the database, and querying the data stored in the database by time.

[0081] When there is no external power supply, the acquisition device 1 and the communication module 2 are powered by the internal lithium battery 13. When there is external power supply, the battery 13 is disconnected from the power supply.

[0082] The main control chip STM32F103VB supports the configuration of low power mode. The system is usually in low power mode and automatically wakes up at specified intervals to collect and store environmental parameters. During low power mode, if the host computer communication wake-up command is received, the original recorded data will be uploaded to the host computer management system immediately, and real-time data collection and transmission will be performed. The ATK-LORA wireless serial communication submodule used has a power saving mode, and the power consumption is as low as 2.3μA when in sleep mode.

[0083] The maintenance reminder function is implemented as follows: the input voltage of the electronic resume system is monitored to identify the power level of the battery 13; the voltage is input into the isolation transmitter for isolation transformation, converted into a 0-5V voltage signal, and sent to the ADC port of the microcontroller for collection; the data management software interprets the monitored data and issues equipment maintenance reminders when it exceeds the specified threshold.

[0084] Through the present invention, the temperature, humidity and pressure inside the aircraft can be collected through the temperature, humidity and pressure sensors of the collection device, and the collected signals are transmitted to the communication module through the connector. The storage chip of the communication module can store multiple pieces of information; the communication module then sends the collected data to the host computer by sending a radio signal through the communication unit, and the communication unit can realize long-distance signal transmission; the host computer stores the data in a database, and the user can use the host computer data management software to query the information stored in the database by time; the present invention also has long-lasting power supply capability and maintenance reminder function.

[0085] The above disclosures are only several specific embodiments of the present invention; however, the present invention is not limited thereto, and any changes that can be conceived by those skilled in the art should fall within the protection scope of the present invention.

Claims

1. An electronic record system for an aircraft, characterized in that: include: A collection device (1), a communication module (2) and a data management system (3); The data collection device (1) is installed inside the aircraft, and comprises a temperature, humidity and pressure sensor (4), an electrical connector (5), a housing (6) (14) and a cover (7). The temperature, humidity and pressure sensor (4) and the electrical connector (5) are installed inside the housing (6), and the cover (7) is installed on the housing (6). A small hole is opened on the cover (7); A communication module (2) is installed outside the aircraft, and comprises a box body (8), a box cover (9), a storage chip (10), a communication unit (11), a printed circuit board (12), a battery (13) and a connector (14); the box cover (9) is installed on the top surface of the box body (8), and the battery (13), the printed circuit board (12), the storage chip (10) and the communication unit (11) are fixedly installed inside the box body (8); the communication unit (11) is used to realize communication with the data management system (3); the connector (14) is extended from the bottom of the box body (8) to connect to the electrical connector (5) of the acquisition device (1); The data management system (3) includes: a host computer, data management software and a database; the data management software is written in Labview language and integrated with the database; the host computer runs the data management software and the database and receives information from the communication module (2); the main functions of the data management software include communication, parameter display, data storage, historical data query, maintenance reminder and downloading of power-on times.

2. The electronic record system for aircraft according to claim 1, characterized in that: The temperature, humidity and pressure sensor (4) in the acquisition device (1) adopts a PCB type temperature, humidity and pressure sensor (4), and outputs the collected temperature, humidity and pressure environmental parameter data according to the Modbus-RTU protocol.

3. The electronic record system for aircraft according to claim 1, characterized in that: The printed circuit board (12) in the communication module (2) comprises a main control circuit, a communication circuit and a storage circuit; The main control circuit includes a main control chip, the embedded software is burned into the main control chip, and the main control chip uses a 32-bit microcontroller STM32F103VB; The communication circuit is connected to the communication unit (11); The storage circuit is connected to the storage chip (10).

4. The electronic record system for aircraft according to claim 3, characterized in that: The main control chip is used for: The 12-bit AD acquisition port of the microcontroller is used to collect the input power supply voltage value to monitor the 27V input power supply voltage, where the voltage signal range is 0~32V; Collecting the temperature, humidity and pressure of the temperature, humidity and pressure sensor (4); The collected temperature, humidity, pressure data and the power-on times information sent by the host computer are stored through the IIC communication protocol; Enable wireless communication.

5. The electronic record system for aircraft according to claim 1, characterized in that: The communication unit (11) uses an ATK-LORA wireless serial port submodule for communication. The submodule is based on a SX1278 radio frequency chip, has a maximum communication distance of 3000m, and an operating frequency band of 410-441Mhz.

6. The aircraft electronic record system according to claim 1, characterized in that: The storage chip (10) adopts a 16M external Flash storage chip (10) and is used for storing environmental parameter information.

7. The aircraft electronic record system according to claim 1, characterized in that: The data storage function of the data management software includes: storing the monitored real-time data in a database, and querying the data stored in the database by time.

8. The aircraft electronic record system according to claim 1, characterized in that: The acquisition device (1) and the communication module (2) are powered by an internal lithium battery (13) when there is no external power supply, and the battery (13) is disconnected from power supply when there is external power supply.

9. The electronic record system for aircraft according to claim 3, characterized in that: The main control chip STM32F103VB supports the configuration of low power consumption mode. The system is usually in low power consumption mode and automatically wakes up at specified intervals to collect and store environmental parameters. During the low power consumption mode, if a communication wake-up command from the host computer is received, the original recorded data is immediately uploaded to the host computer management system, and real-time collection and transmission of data is performed.

10. The aircraft electronic record system according to claim 4, characterized in that: The maintenance reminder function is realized by: monitoring the input voltage of the electronic resume system to identify the power level of the battery (13); inputting the voltage into an isolation transmitter for isolation conversion, converting it into a 0-5V voltage signal, and sending it to the ADC port of the single-chip computer for collection; and interpreting the monitored data with data management software, and issuing a maintenance reminder for the equipment when the data exceeds a specified threshold.

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