Automatic work recording system of electronic equipment for aircraft

Abstract

The invention provides an automatic work recording system and method for electronic equipment for an aircraft, and belongs to the technical field of measurement and control communication, and the system is characterized in that an RC circuit outputs discharge to provide a working voltage for a detection CPU minimum system circuit after the power supply voltage of to-be-detected equipment is closed; the voltage conversion circuit converts the power supply voltage of the to-be-detected device into the input voltage which can be monitored by the detection CPU minimum system circuit and then generates a voltage conversion result. And the CPU minimum system detection circuit monitors the voltage of the to-be-detected equipment according to the voltage conversion result, records the power-on duration when the voltage is greater than a preset threshold value, and stores the power-on duration into the storage circuit within the delay time of the RC delay circuit when the voltage is not greater than the preset threshold value. According to the voltage conversion result, the work of the to-be-tested equipment is automatically recorded, and the working time of the to-be-tested equipment is more accurately recorded, so that the electronic equipment is fully utilized, and the use and maintenance cost of the aircraft is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft measurement and control technology, and particularly to an automatic working recording system for electronic devices used in aircraft. Background Art

[0002] For aircraft, rockets and other aircraft, there are strict requirements for the working time of the electronic devices used. When the working time of the device reaches, the device must be replaced. If the device is not replaced in time, it will ultimately lead to the serious consequence of the aircraft crashing.

[0003] Currently, the monitoring devices for recording the working time of electronic devices on aircraft, rockets and other aircraft are still in a blank state. The maximum service days given by the electronic device manufacturer are mainly used as the basis for judging whether the device is reliable.

[0004] Aircraft, rockets and other aircraft are only powered on during actual flight and ground tests. The actual powered-on working time of the electronic devices in the aircraft does not reach the measurement in days as the minimum unit. The method of calculating the device life in days will cause the situation of premature replacement of electronic devices, and ultimately lead to too high use and maintenance costs of the aircraft under this premise. Summary of the Invention

[0005] In view of the shortcomings of the high use and maintenance costs of existing aircraft, the present invention provides an automatic working recording system for electronic devices used in aircraft. By more accurately recording the working time of the electronic devices, the electronic devices can be made to make the best use of their functions, and the use and maintenance costs of the aircraft are reduced.

[0006] In a first aspect, the present invention provides an automatic working recording system for electronic devices used in aircraft, including: an RC circuit, a voltage conversion circuit, a detection CPU minimum system circuit and a storage circuit;

[0007] The output end of the RC circuit is connected to the first end of the detection CPU minimum system circuit, and is used for outputting a discharge to provide a working voltage for the detection CPU minimum system circuit after the power supply voltage of the device to be measured is turned off;

[0008] The input end of the voltage conversion circuit is connected to the power supply voltage of the device to be measured, and the output end of the voltage conversion circuit is connected to the second end of the detection CPU minimum system circuit, and is used for converting the power supply voltage of the device to be measured into an input voltage that can be monitored by the detection CPU minimum system circuit to obtain a voltage conversion result, and sending it to the detection CPU minimum system circuit.

[0009] Detect the minimum system circuit of the CPU, which is used to monitor the voltage of the device under test according to the voltage conversion result, record the power-on duration when the voltage is greater than the preset threshold, and is also used to store the power-on duration in the storage circuit within the delay time provided by the RC delay circuit when the voltage is not greater than the preset threshold, so as to realize the automatic recording of the operation of the electronic device.

[0010] According to the above-mentioned automatic recording system for the operation of electronic devices for aircraft, it further includes: a serial communication circuit, which is used for external devices to communicate with the minimum system circuit of the detection CPU through the serial port and read out the total power-on operation time of the product recorded in the storage circuit.

[0011] According to the above-mentioned automatic recording system for the operation of electronic devices for aircraft, it further includes: a power supply circuit;

[0012] The power supply circuit is connected between the RC circuit and the minimum system circuit of the detection CPU, and is used for voltage conversion based on the operating voltage of the device under test to provide different supply voltages.

[0013] According to the above-mentioned automatic recording system for the operation of electronic devices for aircraft, the minimum system circuit of the detection CPU includes: a CPU chip with a FLASH, an XADC interface, a UART interface, and an I 2 C interface;

[0014] The CPU chip monitors the input voltage through the XADC interface, uses the internal timer to achieve the precise timing function, and communicates with the memory through the I 2 C interface to realize data reading and writing.

[0015] According to the above-mentioned automatic recording system for the operation of electronic devices for aircraft, the storage circuit includes an E2PROM chip with an I 2 C interface, and the memory is connected to the minimum system circuit of the detection CPU through the I 2 C bus.

[0016] According to the above-mentioned automatic recording system for the operation of electronic devices for aircraft, the RC delay circuit includes a 20K variable resistor and a 100uF variable capacitor.

[0017] On the other hand, the present invention also provides an automatic recording method for the working time of electronic devices for aircraft. Based on any of the above-mentioned automatic recording systems for the operation of electronic devices for aircraft, it includes:

[0018] When the system is powered on, the minimum system circuit of the detection CPU starts to record the power-on time through the internal timer;

[0019] When the system is powered off, the minimum system circuit of the detection CPU monitors whether the input voltage drops to the preset threshold through the XADC interface. If so, it stops recording the power-on time and obtains the working duration before the update;

[0020] The minimum system circuit of the detection CPU reads the historical working duration recorded last time from the storage circuit through the I 2 C interface;

[0021] The minimum system circuit of the detection CPU obtains the updated working duration according to the working duration before update and the historical working duration, and writes the updated working duration into the storage circuit within the delay time provided by the RC delay circuit.

[0022] According to the automatic working recording method of the electronic device for aircraft, the minimum system circuit of the detection CPU uses an internal timer to increment by 1 every second to record the power-on start time.

[0023] The automatic working recording system of the electronic device for aircraft provided by the present invention aims at the disadvantage of too high use and maintenance costs of existing aircraft, and proposes an automatic working recording system of the electronic device for aircraft. After the power supply voltage of the device to be tested is turned off, the RC circuit outputs a discharge to provide a working voltage for the minimum system circuit of the detection CPU. The minimum system circuit of the detection CPU monitors the voltage of the device to be tested, and records the power-on duration when the voltage is greater than the preset threshold. It is also used to store the power-on duration into the storage circuit within the delay time provided by the RC delay circuit when the voltage is not greater than the preset threshold, so as to realize the automatic recording of the working of the electronic device. Through the serial communication circuit, an external device can communicate with the minimum system circuit of the detection CPU through the serial port to read out the total power-on working time of the product recorded in the storage circuit. According to the voltage conversion result, the power-on time is recorded and the power-on time is written into the memory when the power is off, so as to realize the automatic recording of the working of the electronic device. By more accurately recording the working time of the electronic device, the electronic device can be made to make the best use of its functions, and the use and maintenance costs of the aircraft are reduced. Brief Description of the Drawings

[0024] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0025] Figure 1 is one of the schematic structural diagrams of an optional automatic working recording system of the electronic device for aircraft provided by the embodiment of the present invention;

[0026] Figure 2 is the second of the schematic structural diagrams of an optional automatic working recording system of the electronic device for aircraft provided by the embodiment of the present invention. Detailed Embodiment

[0027] To make the objectives, technical solutions, and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below with reference to the accompanying drawings in the present invention. Apparently, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without creative efforts shall fall within the protection scope of the present invention.

[0028] It should be noted that in the description of the embodiments of the present invention, the terms "comprise", "include", or any other variant thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or device that comprises a series of elements includes not only those elements but also other elements that are not explicitly listed, or further includes elements inherent to such process, method, article, or device. Without further limitation, an element defined by the phrase "comprising a..." does not exclude the presence of additional identical elements in the process, method, article, or device that comprises the element. The orientation or positional relationship indicated by terms such as "upper", "lower", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the system or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation to the present invention. Unless otherwise clearly defined and limited, the terms "mount", "connect", and "couple" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0029] The terms "first", "second", etc. in this application are used to distinguish similar objects, rather than to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so that the embodiments of this application can be implemented in an order other than those illustrated or described here, and the objects distinguished by "first", "second", etc. are generally of the same category, and do not limit the number of objects. For example, the first object can be one or multiple. In addition, "and / or" represents at least one of the connected objects, and the character " / " generally represents an "or" relationship between the associated objects before and after.

[0030] Next, with reference to Figure 1 - Figure 2 the automatic working recording system for an electronic device used in an aircraft provided by the embodiments of the present invention will be described.

[0031] Figure 1It is one of the schematic structural diagrams of an optional automatic working recording system for electronic devices used in aircraft provided by an embodiment of the present invention. As Figure 1 shown, an RC circuit, a voltage conversion circuit, a detection CPU minimum system circuit, and a storage circuit;

[0032] The output end of the RC circuit is connected to the first end of the detection CPU minimum system circuit, and is used to output a discharge to provide a working voltage for the detection CPU minimum system circuit after the power supply voltage of the device under test is turned off;

[0033] The input end of the voltage conversion circuit is connected to the power supply voltage of the device under test, and the output end of the voltage conversion circuit is connected to the second end of the detection CPU minimum system circuit. It is used to convert the power supply voltage of the device under test into an input voltage that can be monitored by the detection CPU minimum system circuit to obtain a voltage conversion result, and send it to the detection CPU minimum system circuit.

[0034] The detection CPU minimum system circuit is used to monitor the voltage of the device under test according to the voltage conversion result, record the power-on duration when the voltage is greater than a preset threshold, and is also used to store the power-on duration into the storage circuit within the delay time provided by the RC delay circuit when the voltage is not greater than the preset threshold, so as to realize the automatic recording of the working of the electronic device.

[0035] In an optional embodiment, the RC circuit is the guarantee for realizing the automatic recording of the working time. By using the function that the output of the RC circuit will slowly discharge after the voltage is turned off, it ensures that the relevant systems at the subsequent stage can continue to work. This circuit converts the 28V voltage into a 28V voltage output. When the input voltage of 28V is turned off, its output 28V voltage will not be instantaneously turned off. This is because the circuit utilizes the characteristics of the RC circuit: after the input voltage is turned off, the voltage at its output end (28V) will slowly discharge to 0V. Under this characteristic, the detection CPU minimum system circuit can continue to work for a period of time. During this time, the detection CPU minimum system circuit can complete the monitoring of the voltage drop and write the final working time data into the I2C interface memory at the same time.

[0036] The detection CPU minimum system circuit is the core circuit for realizing the entire function. When specifically implemented, a main control chip with an internal self - contained FLASH, a self - contained XADC interface, a self - contained UART interface, and an I2C interface can be selected for this circuit, and the chip power supply is simple, and it can work with only one type of power supply. There are many chips that meet the above conditions. For example, selecting an STM32 chip (or other 51 single - chip microcomputers that meet the above interfaces) can meet the design requirements.

[0037] The power-off delay function of the RC circuit allows the minimum detection CPU system circuit to continue operating for some time after the 28V voltage is cut off, ensuring that the minimum detection CPU system circuit has sufficient time to record the working time in the memory of the storage circuit.

[0038] The input end of the voltage conversion circuit is connected to the power supply voltage of the device under test, and the output end of the voltage conversion circuit is connected to the second end of the minimum detection CPU system circuit, for converting the power supply voltage of the device under test into an input voltage that can be monitored by the minimum detection CPU system circuit.

[0039] In this embodiment, since the aircraft generally uses 28V for power supply, a voltage conversion circuit is adopted to divide the voltage using a resistor, converting the 28V voltage into a small voltage that can be detected by the CPU in the minimum detection CPU system circuit. Then, the built-in XADC in the main control CPU chip in the minimum detection CPU system circuit monitors the input small voltage.

[0040] Specifically, during this period, when the CPU chip in the minimum detection CPU system circuit detects that the voltage converted by the voltage conversion circuit changes from 3V to 2.35V (since the input 28V voltage usually needs to be divided by a resistor to be converted to 3V, so when it is 22V, the corresponding voltage is 2.35V), the recording function is automatically started, and the power-on working time of the current system is recorded in the I 2 C interface memory of the storage circuit.

[0041] More preferably, according to the RC circuit discharge characteristic formula, specifically:

[0042] Vt = Vc(e (-R1Ct) )

[0043] Among them, Vt is the voltage on the capacitor plate, Vc is the initial capacitor voltage value before attenuation begins. RC represents the time constant (R is the resistance value of the resistor in the RC circuit, C is the capacitance value of the capacitor in the RC circuit).

[0044] According to the formula, when choosing a larger time constant, a variable resistor and a variable capacitor are selected. In this embodiment, a 20K resistor and a 100uF capacitor are used.

[0045] According to the calculation, at 0.48s, the voltage will drop from 28V to 22V; and at 1s, the voltage drops from 28V to about 16.9V. During the time when the voltage drops from 22V to 16V (500ms), according to the circuit design, the entire automatic recording system can still work normally, so it has sufficient time to control the I 2 C interface memory for input reading and writing (because I 2The maximum time for single write or read of the C interface memory is 5 ms).

[0046] After the 28V power supply is turned on, the power-on time record of the CPU chip in the minimum CPU system circuit is started. When the 28V power supply is turned off, due to the power-off delay function of the RC circuit, the minimum CPU system circuit can work for a period of time. During this time, first, it is detected that when the voltage obtained by the voltage conversion circuit in the minimum CPU system circuit drops to 20V, it is considered that the 28V voltage is powered off. Therefore, the power-on time writing function is immediately started, and the memory is controlled to record the power-on time in the memory.

[0047] Preferably, in the present invention, since the main control CPU chip in the minimum CPU system circuit only needs to perform power-on timing and write to the memory when powered off, its software size can be controlled within 64K. Therefore, a low-cost chip in STM32 can be used to implement this function (the low-cost chip comes with internal flash, on-chip XADC, and serial interface), and the functions of controlling the memory and communicating with external devices can be completed without external expansion. The entire minimum CPU detection system circuit is also very simple.

[0048] During use, the input voltage of the entire system and the input voltage of the device to be monitored are connected together, and the entire system is powered by the RC circuit inside the device. When the CPU in the minimum CPU system circuit is powered on, the power-on time recording is started. The timer increments by 1 per second, and the internal XADC interface is used to continuously monitor whether the input voltage is lower than 20V. Once the input voltage is lower than 20V, the recording function is started, and the recorded power-on time is written into the memory of the storage circuit.

[0049] Through the above method, the automatic recording function of the power-on time of the device is realized during the 28V power-off process. Since the entire system requires very few chips and has the characteristic of small size (the size of the entire system can be made within 4 cm (length) × 4 cm (width) × 3 cm (height)), it can be placed at any position inside the aircraft.

[0050] The storage circuit is used to receive the write instruction sent by the minimum CPU detection system circuit to control the storage circuit and store the power-on working time data of the device to be tested.

[0051] In this embodiment, the memory in the storage circuit is controlled by the minimum CPU detection system circuit to record the power-on working time data of the product.

[0052] Figure 2 It is the second structural schematic diagram of an optional automatic recording system for the working of an aircraft electronic device provided by an embodiment of the present invention, as Figure 2As shown, the present invention provides an automatic recording system for electronic equipment operation for aircraft, which also includes:

[0053] The serial communication circuit is used to communicate with external test equipment. It can send the power-on time in the I2C memory to the external test equipment. After testing, the time is used as the basis for whether the corresponding electronic equipment on the aircraft needs to be replaced. The serial communication circuit can use a low-cost RS232 interface chip. In addition, the RS232 interface chip without an isolation interface can realize the relevant functions.

[0054] In this embodiment, the serial communication circuit mainly includes the resistors and capacitors required by the RS232 serial transceiver circuit, which can convert the UART interface level of the CPU chip in the detection CPU minimum system circuit into the RS232 serial communication level for data interaction with external designs. There are many types of RS232 chips. In the present invention, the MAX232 chip (non-isolated chip) is selected for design, and the isolated chip ADM3251 can also be selected for design according to specific circumstances.

[0055] In one embodiment, the present invention provides a method for automatically recording the working time of electronic equipment for aircraft. Based on the above-mentioned automatic recording system for the working time of electronic equipment for aircraft, the method includes:

[0056] When the system is powered on, the CPU minimum system circuit starts recording the power-on time through the internal timer;

[0057] When the system is powered off, the CPU minimum system circuit is detected to monitor whether the input voltage drops to the preset threshold through the XADC interface. If so, the power-on time is stopped to obtain the working time before the update;

[0058] Detect CPU minimum system circuit through I 2 The C interface reads the last recorded historical working time from the storage circuit;

[0059] The CPU minimum system circuit is detected to obtain the updated working time according to the working time before updating and the historical working time, and write the updated working time into the storage circuit within the delay time provided by the RC delay circuit.

[0060] Furthermore, the CPU minimum system circuit is detected by adding 1 per second through an internal timer to record the power-on start time.

[0061] according to Figure 1 The principle block diagram shown is used to design the PCB of the automatic recording system of the working time of the electronic equipment used in the aircraft;

[0062] Connect the 28V input voltage of the electronic device to be recorded to the system;

[0063] After the product is powered on, the recording system works normally. The CPU chip in the minimum system circuit of the detection CPU will record the power-on time T1 (using the timer in the chip to increment by 1 per second).

[0064] When the input 28V voltage of the electronic device is turned off, due to the discharging effect of the RC circuit, the entire recording system will not immediately lose power and stop working, but can continue to work for a period of time.

[0065] After that, when the CPU chip in the minimum system circuit of the detection CPU monitors that the 28V voltage drops to 22V, that is, when the voltage it collects changes from 3V to 2.35V after passing through the voltage conversion circuit, it starts the automatic recording function.

[0066] The CPU chip in the minimum system circuit of the detection CPU first reads the previously recorded power-on working time T2 from the I2C interface memory of the storage circuit, adds the power-on time T1 recorded by the CPU chip and the previously recorded power-on working time T2 read from the I2C interface memory to obtain the latest working time T3.

[0067] Finally, the CPU chip in the minimum system circuit of the detection CPU records the latest working time T3 into the I2C interface memory through the I2C bus.

[0068] The serial communication circuit communicates with an external test device and can send the power-on time in the I2C memory to the external test device. After testing this time, it is used as the basis for whether to replace the corresponding electronic device on the aircraft.

[0069] Optionally, the storage circuit mainly selects an I 2 C interface memory and the required external resistors and capacitors. This circuit is interconnected with the I 2 C interface of the CPU chip in the minimum system circuit of the detection CPU. By controlling the I 2 C interface of the CPU chip through software programs, it is possible to write the product power-on working time into the I 2 C interface memory of the storage circuit, or read the product power-on working time from the I 2 C interface memory of the storage circuit. In one implementation, an I I C interface memory of ST's M24C01-W can be selected. This memory has a write life of more than 4 million times and can store data for more than 200 years, which can meet the actual use.

[0070] The system embodiments described above are merely illustrative. The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art can understand and implement it without creative efforts.

[0071] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on such an understanding, the essence of the above technical solution, or the part that contributes to the prior art, can be embodied in the form of a software product. The computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to enable a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0072] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. And these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An automatic recording system for electronic equipment operation of an aircraft, comprising: RC circuit, voltage conversion circuit, CPU minimum system detection circuit and storage circuit; The output end of the RC circuit is connected to the first end of the CPU minimum system circuit for detecting the CPU, and is used for outputting discharge to provide a working voltage for the CPU minimum system circuit for detecting the CPU after the power supply voltage of the device under test is turned off; The input end of the voltage conversion circuit is connected to the power supply voltage of the device under test, and the output end of the voltage conversion circuit is connected to the second end of the detection CPU minimum system circuit, and is used to convert the power supply voltage of the device under test into an input voltage that can be monitored by the detection CPU minimum system circuit to obtain a voltage conversion result, and send it to the detection CPU minimum system circuit; The CPU minimum system circuit is detected, which is used to monitor the voltage of the device under test according to the voltage conversion result, record the power-on time when the voltage is greater than the preset threshold, and store the power-on time in the storage circuit within the delay time provided by the RC delay circuit when the voltage is not greater than the preset threshold, so as to realize automatic recording of the operation of the electronic device.

2. The automatic recording system for aircraft electronic equipment according to claim 1, characterized in that: Also includes: The serial port communication circuit is used for external equipment to communicate with the detection CPU minimum system circuit through the serial port, and read out the total power-on working length of the product recorded in the storage circuit.

3. The automatic recording system for aircraft electronic equipment according to claim 1, characterized in that: Also includes: Power supply circuit; The power supply circuit is connected between the RC circuit and the detection CPU minimum system circuit, and is used to perform voltage conversion based on the working voltage of the device to be tested to provide different power supply voltages.

4. The automatic recording system for aircraft electronic equipment according to claim 1, characterized in that: The detection CPU minimum system circuit includes: FLASH, XADC interface, UART interface and I 2 C interface CPU chip; The CPU chip monitors the input voltage through the XADC interface, uses the internal timer to achieve accurate timing, and 2 C interface communicates with the memory to realize the reading and writing of data.

5. The automatic recording system for aircraft electronic equipment according to claim 1, characterized in that: The storage circuit includes I 2 C interface E2PROM chip, the memory is connected through I 2 C bus is connected to the minimum system circuit of the detection CPU.

6. The automatic recording system for aircraft electronic equipment according to claim 1, characterized in that: The RC delay circuit includes a 20K variable resistor and a 100uF variable capacitor.

7. A method for automatically recording the working time of electronic equipment for aircraft, based on the automatic working time recording system for electronic equipment for aircraft as claimed in any one of claims 1 to 6, characterized in that: include: When the system is powered on, the CPU minimum system circuit starts recording the power-on time through the internal timer; When the system is powered off, the CPU minimum system circuit is detected to monitor whether the input voltage drops to the preset threshold through the XADC interface. If so, the power-on time is stopped to obtain the working time before the update; Detect CPU minimum system circuit through I 2 The C interface reads the last recorded historical working time from the storage circuit; The CPU minimum system circuit is detected to obtain the updated working time according to the working time before updating and the historical working time, and write the updated working time into the storage circuit within the delay time provided by the RC delay circuit.

8. The method for automatically recording the operation of electronic equipment for aircraft according to claim 7, characterized in that: The CPU minimum system circuit detects the internal timer, which increases by 1 per second to record the power-on start time.

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