Power supply state reporting method realized based on hardware

Abstract

The invention belongs to the technical field of airborne electronic systems, and particularly relates to a hardware-based power supply state reporting method, which is used for reporting the power supply state of an airborne electronic system and is realized based on a power supply processing and power failure protection system. A power factor correction circuit, a voltage detection circuit, an energy storage capacitor, a direct-current conversion circuit and an early warning signal generation circuit are arranged in the power supply processing and power failure protection system, a state reporting method is provided for a high-safety system, the state reporting method can be achieved through pure hardware under the condition that software is not used, and program burning and upgrading maintenance are not needed.

Description

Technical Field

[0001] The invention belongs to the technical field of airborne electronic systems, and in particular relates to a power status reporting method based on hardware implementation. Background Art

[0002] With the development of technology and the increasing complexity of the environment, aircraft have higher and higher requirements for the safety and reliability of airborne electronic systems, requiring components to ensure their core functions under various adverse conditions and report the working status of components to the airborne electronic control system in a timely manner.

[0003] The functions of the status reporting method are: 1. Prevent the core equipment of the system from terminating due to power undervoltage or instantaneous power failure, which affects safety. 2. Prevent important data in flight from not being recorded or saved due to special circumstances such as unexpected power failure.

[0004] The existing technology realizes the status reporting function by using the digital-to-analog conversion circuit, the digital interface circuit and the chip together. There are the following disadvantages: it involves software communication protocols, the analog circuit and the digital circuit need to be isolated, and the development and design verification process is relatively complicated; it is not highly compatible with the system input power supply voltage range, and exceeding the range will cause the digital devices that are more sensitive to voltage to fail; if the digital circuit fails, the module needs to be disassembled and the program file needs to be re-burned with a dedicated burning device, which is difficult to operate in the field, affecting the maintainability of the product. Summary of the invention

[0005] In view of this, the present invention provides a power status reporting method based on hardware implementation, which is used for reporting the power status of an airborne electronic system and can solve at least part of the above-mentioned technical problems.

[0006] The specific technical solution adopted by the present invention is:

[0007] A power status reporting method based on hardware implementation is used for power status reporting of an airborne electronic system, and the status reporting method is implemented based on a power processing and power failure protection system;

[0008] The power supply processing and power-off protection system is provided with:

[0009] A power factor correction circuit is connected to the aircraft power supply end and is used to rectify the single-phase AC power input from the aircraft power supply end into a DC power supply;

[0010] A voltage detection circuit detects the voltage value of the single-phase AC power input from the aircraft power supply terminal and the DC power output from the power factor correction circuit;

[0011] Energy storage capacitor, using high voltage capacitor to store energy of DC power output by power factor correction circuit;

[0012] The DC conversion circuit converts the DC power output by the power factor correction circuit into various voltages required by the main control system;

[0013] The early warning signal generating circuit has an input end connected to a voltage detection circuit and an energy storage capacitor, and an output end connected to a main control system. If the voltage amplitude is lower than a preset voltage threshold value during real-time detection, it is determined that the aircraft power supply end is in an undervoltage state; if the undervoltage state lasts for more than a preset time threshold value, it is determined that the aircraft power supply end is in a power-off state.

[0014] Furthermore, the preset time threshold is 200ms.

[0015] Furthermore, the DC conversion circuit is configured as a dual backup output.

[0016] Furthermore, the reporting method includes:

[0017] After the system is powered on or reset, the voltage detection circuit first detects whether the input voltage reaches the start-up threshold voltage. If it is lower than the threshold voltage, the main control system will not start and remain in the shutdown state; if it is higher than the threshold voltage, the main control system will start and operate normally;

[0018] While the system is running, if any abnormality occurs in any DC conversion circuit of the power processing and power-off protection system, the dual backup output of the DC conversion circuit will continue to supply power to the main control system and report the fault information to the main control system.

[0019] Furthermore, when the aircraft power supply unexpectedly loses power, the main control system is powered for a short time based on the energy storage capacitor. The main control system receives an early warning signal and immediately performs power-off protection, and important data is recorded and saved.

[0020] Furthermore, after important data records are saved, the main control system is powered off and shut down.

[0021] The beneficial effects of the present invention are:

[0022] 1. The present invention provides a status reporting method for a high-security system, which can be implemented purely by hardware without using software, and does not require program burning and upgrade maintenance;

[0023] 2. The development process of the present invention is simple, no computer is required, and all functions can be automatically completed when powered on;

[0024] 3. The present invention is highly safe and can avoid accidents caused by failure of core functions when the system loses power unexpectedly;

[0025] 4. The present invention has high reliability and can avoid the loss of important data when the system loses power unexpectedly;

[0026] 5. The present invention can prevent software from being locked. When the power is off for 200 milliseconds, the software determines that the system should enter the shutdown state. At this time, if the power is turned on again, the system can resume normal operation. The software will mistakenly determine that the system is shut down, thereby locking. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0028] Figure 1 It is a hardware system block diagram of a power status reporting method based on hardware implementation in a specific implementation mode of the present invention;

[0029] Figure 2 The figure is a flowchart of a power status reporting method based on hardware implementation in a specific embodiment of the present invention. DETAILED DESCRIPTION

[0030] The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.

[0031] The following describes the embodiments of the present disclosure through specific examples, and those skilled in the art can easily understand other advantages and effects of the present disclosure from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all of the embodiments. The present disclosure can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present disclosure. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present disclosure.

[0032] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present disclosure, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0033] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present disclosure. The illustrations only show components related to the present disclosure rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0034] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

[0035] In one embodiment of the present invention, a power status reporting method based on hardware implementation is proposed, which is used for power status reporting of an airborne electronic system. The status reporting method is implemented based on a power processing and power failure protection system;

[0036] The power supply processing and power-off protection system is provided with:

[0037] A power factor correction circuit is connected to the aircraft power supply end and is used to rectify the single-phase AC power input from the aircraft power supply end into a DC power supply;

[0038] A voltage detection circuit detects the voltage value of the single-phase AC power input from the aircraft power supply terminal and the DC power output from the power factor correction circuit;

[0039] Energy storage capacitor, using high voltage capacitor to store energy of DC power output by power factor correction circuit;

[0040] The DC conversion circuit converts the DC power output by the power factor correction circuit into various voltages required by the main control system;

[0041] The early warning signal generating circuit has an input end connected to a voltage detection circuit and an energy storage capacitor, and an output end connected to a main control system. If the voltage amplitude is lower than a preset voltage threshold value during real-time detection, it is determined that the aircraft power supply end is in an undervoltage state; if the undervoltage state lasts for more than a preset time threshold value, it is determined that the aircraft power supply end is in a power-off state.

[0042] In this embodiment, the preset time threshold is 200 ms.

[0043] In this embodiment, the DC conversion circuit is configured as a dual backup output.

[0044] In this embodiment, the reporting method includes:

[0045] After the system is powered on or reset, the voltage detection circuit first detects whether the input voltage reaches the start-up threshold voltage. If it is lower than the threshold voltage, the main control system will not start and remain in the shutdown state; if it is higher than the threshold voltage, the main control system will start and operate normally;

[0046] While the system is running, if any abnormality occurs in any DC conversion circuit of the power processing and power-off protection system, the dual backup output of the DC conversion circuit will continue to supply power to the main control system and report the fault information to the main control system.

[0047] In this embodiment, when the aircraft power supply unexpectedly loses power, the main control system is powered for a short time based on the energy storage capacitor. The main control system receives an early warning signal and immediately performs power-off protection, and records and saves important data.

[0048] In this embodiment, after important data records are saved, the main control system is powered off and shut down.

[0049] This embodiment can ensure the normal operation of the core functions of the airborne electronic system and report the working status to the airborne electronic main control system under the following circumstances: 1. The 115V single-phase AC power supply has a power outage or undervoltage surge lasting up to 200 milliseconds, 2. The power factor correction circuit fails, 3. Part of the DC conversion circuit fails.

[0050] In this embodiment, when the 115V single-phase AC power supply unexpectedly loses power or shuts down, an early warning signal is issued, and the energy output is maintained for 200 milliseconds to allow the main control system to record and save important data and shut down in an orderly manner.

[0051] This embodiment uses only hardware to implement the detection and reporting functions, has stronger compatibility, and a more flexible development and design process.

[0052] This embodiment is adaptive to a wide range of input voltage, and the system can operate stably as long as the minimum voltage reaches 65Vrms; when the system is transiently powered off (within 200ms), the system can operate stably; in the event of partial failure of the power supply circuit, the normal operation of the core functions of the onboard electronic system is ensured; before the equipment is shut down due to power outage, the power-off warning signal can be reported to the main control system, and a buffer time is provided to allow the main control system to record or save important data.

[0053] Figure 1 The system block diagram of this embodiment is shown. The entire system includes an aircraft power supply end, a power supply processing and power failure protection system, and a main control system. The entire energy flow is from left to right. The aircraft power supply is 115V AC power, which is transmitted to the power supply processing and power failure protection system. After being processed by the power supply processing and power failure protection system, a DC voltage and a warning / normal working signal are provided to the subsequent main control system. The main control system responds according to the signal, whether to record important data and shut down.

[0054] The power supply processing and status reporting system includes a power factor correction circuit, a voltage detection circuit, an energy storage capacitor, a DC conversion circuit, a dual backup of the output voltage, and a warning signal generation circuit. The single-phase 115V AC input power supply is rectified into a DC voltage after power factor correction. The large-capacity energy storage capacitor can store electrical energy and provide energy for the subsequent equipment when the 115V input power supply loses power instantly. The voltage detection circuit is used to detect the effective value of the voltage at the input end in real time, and triggers a warning signal when it is lower than a certain value; the warning signal generation circuit is used to report two signals, "normal operation" and "power-off warning", to the main control system. The dual backup of the output voltage is used to output a stable voltage value when part of the internal circuit of the DC conversion circuit fails.

[0055] Figure 2 Shown is a flow chart of a status reporting method according to an embodiment of the present invention.

[0056] After the system is powered on or reset, the voltage detection circuit first detects whether the input voltage reaches the start-up threshold voltage of 65Vrms. If it is lower than the threshold voltage, the main control system will not start and remain in the shutdown state. If it is higher than the threshold voltage, the main control system starts and operates normally. While the system is running, if there are abnormalities in the DC conversion circuits of the power processing and power-off protection systems, the main control system can still be powered on due to the existence of dual backup of the output voltage, and the fault information is reported to the main control system. The system receives the signal and responds, and can provide a basis for maintenance after the power is cut off.

[0057] When power is accidentally cut off, the presence of large-capacity energy storage capacitors can maintain power supply to the main control system for 200ms. During this shutdown buffer time, the main control continues to work, and at the same time receives an early warning signal and immediately performs power-off protection, and records and saves important data. After 200ms, the system officially powers off and shuts down, realizing power-off protection and power-off buffering, and providing reliability and security for the entire system.

[0058] The above is only a specific implementation of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present disclosure should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. A power status reporting method based on hardware implementation, used for power status reporting of an airborne electronic system, characterized in that: The status reporting method is implemented based on the power supply processing and power-off protection system; The power supply processing and power-off protection system is provided with: A power factor correction circuit is connected to the aircraft power supply end and is used to rectify the single-phase AC power input from the aircraft power supply end into a DC power supply; A voltage detection circuit detects the voltage value of the single-phase AC power input from the aircraft power supply terminal and the DC power output from the power factor correction circuit; Energy storage capacitor, using high voltage capacitor to store energy of DC power output by power factor correction circuit; The DC conversion circuit converts the DC power output by the power factor correction circuit into various voltages required by the main control system; The early warning signal generating circuit has an input end connected to a voltage detection circuit and an energy storage capacitor, and an output end connected to a main control system. If the voltage amplitude is lower than a preset voltage threshold value during real-time detection, it is determined that the aircraft power supply end is in an undervoltage state; if the undervoltage state lasts for more than a preset time threshold value, it is determined that the aircraft power supply end is in a power-off state.

2. The method for reporting power status based on hardware implementation according to claim 1, characterized in that: The preset time threshold is 200ms.

3. The method for reporting power status based on hardware implementation according to claim 2, characterized in that: The DC conversion circuit is set to dual backup output.

4. The method for reporting power status based on hardware implementation according to claim 3, characterized in that: The reporting method includes: After the system is powered on or reset, the voltage detection circuit first detects whether the input voltage reaches the start-up threshold voltage. If it is lower than the threshold voltage, the main control system will not start and remain in the shutdown state; if it is higher than the threshold voltage, the main control system will start and operate normally; While the system is running, if any abnormality occurs in any DC conversion circuit of the power processing and power-off protection system, the dual backup output of the DC conversion circuit will continue to supply power to the main control system and report the fault information to the main control system.

5. The method for reporting power status based on hardware implementation according to claim 4, characterized in that: When the aircraft power supply unexpectedly loses power, the main control system is powered for a short time based on the energy storage capacitor. The main control system receives an early warning signal and immediately performs power-off protection, and records and saves important data.

6. The method for reporting power status based on hardware implementation according to claim 5, characterized in that: After important data records are saved, the main control system is powered off and shut down.

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