Aircraft ignition device, aircraft ignition method and related equipment

Abstract

The invention relates to an aircraft ignition device, an aircraft ignition method and related equipment, and relates to the technical field of aircrafts. The aircraft ignition device comprises an ignition control module used for receiving an ignition instruction and correspondingly generating an ignition signal so as to activate a corresponding initiating explosive device assembly or a battery assembly on an aircraft; the ignition instruction input detection module is used for receiving an ignition instruction to output an ignition instruction detection result and sending the ignition instruction detection result to a remote measurement system or a comprehensive measurement system corresponding to the aircraft; and the ignition signal output detection module is used for receiving the ignition signal to output an ignition signal detection result and sending the ignition signal detection result to a remote measurement system or a comprehensive measurement system. According to the aircraft ignition device, the ignition function is met, meanwhile, the ignition process is comprehensively monitored and managed, and the reliability, safety and intelligent degree of the aircraft ignition device in the operation process are improved.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft ignition device, an aircraft ignition method and related equipment. Background Art

[0002] With the continuous development of aviation and aerospace technology, aircraft electrical systems are evolving towards miniaturization, integration and intelligence. This trend not only improves the performance and reliability of the system, but also enhances the adaptability of aircraft in complex environments. As a key component in the electrical control system of an aircraft, the function of the aircraft ignition module / device is directly related to the success of the flight mission.

[0003] The aircraft ignition device in the related art mainly integrates the ignition function into the module, which is used to activate the corresponding pyrotechnic components on the aircraft, making the entire aircraft electrical system more compact and efficient. Although the above design meets the basic ignition requirements, it has the defect of single function and cannot meet the modern aircraft's requirements for high reliability, safety, versatility, flexibility and intelligence, and it is difficult to cope with increasingly complex flight missions.

[0004] Currently, no effective solution has been proposed to the problems of single function, poor reliability and safety, and low intelligence level of aircraft ignition devices in related technologies. Summary of the invention

[0005] An aircraft ignition device, an aircraft ignition method and related equipment provided by the embodiments of the present invention at least solve the problems of the aircraft ignition device in the related art, such as single function, poor reliability and safety, and low intelligence.

[0006] In order to solve the above problems, one aspect of an embodiment of the present invention provides an aircraft ignition device, including an ignition control module, an ignition instruction input detection module, and an ignition signal output detection module, wherein:

[0007] An ignition control module is used to receive external ignition instructions Z1-Zn, and generate ignition signals T1-Tn according to the ignition instructions Z1-Zn, so as to activate the corresponding pyrotechnic components or battery components on the aircraft respectively; wherein n is the number of components to be activated corresponding to the aircraft;

[0008] An ignition command input detection module is used to receive external ignition commands Z1-Zn, output an ignition command detection result Zq presented as a first voltage signal according to the ignition commands Z1-Zn, and send the ignition command detection result Zq to a telemetry system or a comprehensive measurement system corresponding to the aircraft; wherein different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition commands Z1-Zn;

[0009] The ignition signal output detection module is used to receive the ignition signal T1-Tn, output the ignition signal detection result Tq in the form of a second voltage signal according to the ignition signal T1-Tn, and send the ignition signal detection result Tq to the telemetry system or the integrated measurement system; wherein different voltage amplitudes in the second voltage signal are used to respectively characterize the output states of the ignition signals T1-Tn.

[0010] In some of the embodiments, the device further comprises an on-board power supply monitoring module, a computer module and a bus isolation module; wherein,

[0011] The missile power supply monitoring module is used to isolate and receive the power supply voltage values ​​corresponding to the missile power supplies V1-Vm on the aircraft, and convert the power supply voltage values ​​into output voltage signals U1-Um that share the same ground with the computer module power supply; where m is the number of missile power supplies corresponding to the aircraft;

[0012] A computer module, used for receiving the output voltage signal U1-Um, packaging the output voltage signal U1-Um into monitoring information Dq, and sending the monitoring information Dq to the bus isolation module;

[0013] The bus isolation module is used to electrically isolate the received monitoring information Dq to obtain isolated monitoring information Dgq, and send the isolated monitoring information Dgq to the flight management module.

[0014] In some of the embodiments, the computer module is further configured to:

[0015] Receive the ignition command detection result Zq sent by the ignition command input detection module and the ignition signal detection result Tq sent by the ignition signal output detection module, and pack the ignition command detection result Zq, the ignition signal detection result Tq and the output voltage signal U1-Um into the monitoring information Dq.

[0016] In some of the embodiments, a temperature sensor is integrated in the computer module, and the temperature sensor is used to obtain temperature information of the aircraft. The computer module is also used to package the temperature information into the monitoring information Dq.

[0017] In some of the embodiments, an analog-to-digital converter is integrated in the computer module, and the analog-to-digital converter is used to convert a voltage signal received by the computer module into a digital signal.

[0018] In some of the embodiments, an isolation amplifier is integrated in the elastic power supply monitoring module, which receives the power supply voltage values ​​corresponding to the power supplies V1-Vm through the isolation amplifier, and converts the power supply voltage values ​​into output voltage signals U1-Um which are shared with the power supply of the computer module; wherein the amplitude corresponding to the output voltage signal U1-Um is within the analog value acquisition range of the analog-to-digital converter.

[0019] In order to solve the above problems, one aspect of an embodiment of the present invention provides an aircraft ignition method, which is applied to any of the above aircraft ignition devices, and the method includes:

[0020] The ignition control module based on the aircraft ignition device receives the external ignition instructions Z1-Zn, and generates ignition signals T1-Tn according to the ignition instructions Z1-Zn to activate the corresponding pyrotechnic components or battery components on the aircraft respectively; wherein n is the number of components to be activated on the aircraft;

[0021] An ignition command input detection module based on an aircraft ignition device receives an external ignition command Z1-Zn, outputs an ignition command detection result Zq presented as a first voltage signal according to the ignition command Z1-Zn, and sends the ignition command detection result Zq to a telemetry system or a comprehensive measurement system corresponding to the aircraft; wherein different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition commands Z1-Zn;

[0022] An ignition signal output detection module based on an aircraft ignition device receives an ignition signal T1-Tn, outputs an ignition signal detection result Tq presented as a second voltage signal according to the ignition signal T1-Tn, and sends the ignition signal detection result Tq to a telemetry system or an integrated measurement system; wherein different voltage amplitudes in the second voltage signal are used to respectively characterize the output states of the ignition signals T1-Tn.

[0023] In some embodiments, the aircraft ignition device further includes an onboard power supply monitoring module, a computer module, and a bus isolation module; and the method further includes:

[0024] Based on the on-board power supply monitoring module, the power supply voltage values ​​corresponding to the number of on-board power supplies V1-Vm on the aircraft are isolated and received, and the power supply voltage values ​​are converted into output voltage signals U1-Um that share the same ground with the computer module power supply; wherein m is the number of on-board power supplies corresponding to the aircraft;

[0025] Based on the computer module receiving the output voltage signal U1-Um, the output voltage signal U1-Um is packaged into the monitoring information Dq, and the monitoring information Dq is sent to the bus isolation module;

[0026] Based on the bus isolation module, the received monitoring information Dq is electrically isolated to obtain isolated monitoring information Dgq, and the isolated monitoring information Dgq is sent to the flight management module.

[0027] In order to solve the above problems, one aspect of an embodiment of the present invention provides an electronic device, including: a processor, and a memory storing a program, wherein the program includes instructions, and when the instructions are executed by the processor, the processor executes any one of the above-mentioned aircraft ignition methods.

[0028] In order to solve the above problems, one aspect of an embodiment of the present invention provides a non-transitory machine-readable medium storing computer instructions, where the computer instructions are used to enable a computer to execute any of the above-mentioned aircraft ignition methods.

[0029] Beneficial effects of the embodiments of the present invention: by adopting an aircraft ignition device including an ignition control module, an ignition instruction input detection module, and an ignition signal output detection module; wherein: the ignition control module is used to receive external ignition instructions Z1-Zn, and generate ignition signals T1-Tn according to the ignition instructions Z1-Zn, so as to respectively activate the corresponding pyrotechnic components or battery components on the aircraft; wherein n is the number of components to be activated on the aircraft; the ignition instruction input detection module is used to receive external ignition instructions Z1-Zn, and output the first voltage signal according to the ignition instructions Z1-Zn The ignition command detection result Zq is obtained, and the ignition command detection result Zq is sent to the telemetry system or integrated measurement system corresponding to the aircraft; wherein the different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition commands Z1-Zn; an ignition signal output detection module is used to receive the ignition signals T1-Tn, output the ignition signal detection result Tq presented as a second voltage signal according to the ignition signals T1-Tn, and send the ignition signal detection result Tq to the telemetry system or integrated measurement system; wherein the different voltage amplitudes in the second voltage signal are used to respectively characterize the output states of the ignition signals T1-Tn. By integrating the ignition control module, the ignition command input detection module and the ignition signal output detection module in the aircraft ignition device, the ignition function can be satisfied through the ignition control module, and the status of the ignition command and the ignition signal can be detected before the aircraft is launched through the ignition command input detection module and the ignition signal output detection module, thereby satisfying the self-inspection function of the aircraft before launch, realizing comprehensive monitoring and management of the ignition process, and improving the reliability and safety of the aircraft ignition device during operation. Based on the intelligent monitoring of the aircraft ignition process, the intelligence level of the aircraft ignition operation is improved, achieving the technical effect of further promoting the miniaturization, integration and intelligent development of the aircraft.

[0030] The details of one or more embodiments of the invention are set forth in the following drawings and description so that other features, objects, and advantages of the invention are more readily apparent. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the prior art descriptions. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other embodiments can be obtained based on these drawings without creative work.

[0032] Figure 1 It is a schematic diagram of the functional module framework of an aircraft ignition device according to an embodiment of the present invention.

[0033] Figure 2 It is a schematic diagram of the functional module framework of an aircraft ignition device according to another embodiment of the present invention.

[0034] Figure 3 It is a circuit diagram of an aircraft ignition device according to an embodiment of the present invention.

[0035] Figure 4 It is a schematic diagram of the main process of an aircraft ignition method according to an embodiment of the present invention.

[0036] Figure 5 It is a structural schematic diagram of the electronic device of the present invention. DETAILED DESCRIPTION

[0037] Embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present invention. It should be understood that the drawings and embodiments of the present invention are only for exemplary purposes and are not intended to limit the scope of protection of the present invention.

[0038] In the fields of aviation and aerospace, miniaturization, integration, and intelligence are the development direction of electrical systems on aircraft. Integrating the ignition function of the aircraft into the aircraft ignition module / device is one of the development results. The aircraft ignition device in the related technology is simply used to execute the activation of various functional components of the aircraft electrical control system, without considering the self-inspection of key electrical characteristics after the aircraft is powered on. There are problems such as single function, insufficient safety and intelligence. Before the aircraft is launched, self-checking as much internal information of the aircraft as possible, monitoring other states of the electrical system, and sending the real-time monitoring results to the flight management module for analysis can ensure the reliability and safety of the aircraft electrical system and ensure a successful launch.

[0039] In order to solve the above problems, an embodiment of the present invention provides an aircraft ignition device, such as Figure 1As shown, the aircraft ignition device mainly includes: an ignition control module, an ignition command input detection module, and an ignition signal output detection module, wherein: the ignition control module is used to receive external ignition commands Z1-Zn, and generate ignition signals T1-Tn according to the ignition commands Z1-Zn, so as to respectively activate the corresponding pyrotechnic components or battery components on the aircraft; wherein n is the number of components to be activated on the aircraft; the ignition command input detection module is used to receive external ignition commands Z1-Zn, and output ignition commands presented as first voltage signals according to the ignition commands Z1-Zn. The detection result Zq is sent to the telemetry system or the integrated measurement system corresponding to the aircraft; wherein the different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition commands Z1-Zn; an ignition signal output detection module is used to receive the ignition signals T1-Tn, output the ignition signal detection result Tq presented as a second voltage signal according to the ignition signals T1-Tn, and send the ignition signal detection result Tq to the telemetry system or the integrated measurement system; wherein the different voltage amplitudes in the second voltage signal are used to respectively characterize the output states of the ignition signals T1-Tn.

[0040] Based on the aircraft ignition device provided by the embodiment of the present invention, by introducing the ignition command input detection module and the ignition signal output detection module, comprehensive monitoring and management of the ignition process is achieved, which significantly improves the reliability, real-time monitoring capability and intelligence level of the aircraft electrical system. At the same time, modular design and unified voltage signal standards also facilitate the integration and maintenance of the system, and provide a solid guarantee for the safe launch of the aircraft.

[0041] Specifically, the ignition control module automatically generates the corresponding ignition signal according to the received ignition command, and automatically detects and feedbacks, which reduces the need for manual intervention and improves the automation level of the aircraft electrical system. Through the setting of the ignition command input detection module and the ignition signal output detection module, the dual detection of the ignition command Z1-Zn and the ignition signal T1-Tn is realized, which not only ensures the accuracy of the command reception, but also verifies the successful generation and transmission of the ignition signal, thereby improving the reliability of the entire ignition process. The ignition command detection result Zq and the ignition signal detection result Tq are sent to the telemetry system or the comprehensive measurement system in a timely manner, realizing real-time monitoring of the ignition process, facilitating subsequent data analysis and troubleshooting, and also allowing the ground control center to immediately understand the ignition status, respond quickly, and take measures to adjust or terminate the operation when necessary.

[0042] Among them, the different voltage amplitudes in the ignition command detection result Zq and the ignition signal detection result Tq presented as voltage signals are used to characterize the status of the ignition command and the ignition signal, making the status information more intuitive and easy to identify, reducing the possibility of misjudgment and enhancing the stability and safety of the system. Based on the different voltage amplitudes of the first voltage signal and the second voltage signal, the aircraft electrical system can realize intelligent diagnosis of the ignition command and the ignition signal status. For example, an abnormal voltage amplitude may indicate a potential problem, such as a line fault or component failure, which is helpful for early warning and preventive maintenance.

[0043] According to a specific implementation of the embodiment of the present invention, Figure 3 As shown (it should be noted that Figure 3 Only one ignition instruction T1 and an ignition signal T1 corresponding to the ignition instruction are marked, and the other instructions / signals are not marked in the figure). The ignition control module can receive external ignition instructions Z1-Zn through a photoelectric coupler, and output corresponding ignition signals T1-Tn, wherein the ignition signals T1-Tn can be used to activate the corresponding pyrotechnics or batteries on the aircraft, respectively, to realize the main ignition function of the aircraft ignition device. The ignition instruction input detection module can receive external ignition instructions Z1-Zn through a photoelectric coupler, and output corresponding ignition instruction monitoring results Zq, wherein Zq is a voltage signal, and different voltage amplitudes can represent the input state of the external ignition instructions Z1-Zn. The ignition signal output detection module can receive ignition signals T1-Tn through a photoelectric coupler, and output corresponding ignition signal monitoring results Tq, wherein Tq is a voltage signal, and different voltage amplitudes can represent the output state of the external ignition signals T1-Tn.

[0044] In some of the embodiments, the separate design of the ignition control module, the ignition command input detection module and the ignition signal output detection module enables each functional module to be independently developed and tested, simplifying system integration and maintenance. At the same time, due to the use of a unified voltage signal standard, the design has good scalability and compatibility, is easy to integrate with other aircraft electrical systems, and supports the needs of different models of aircraft. Furthermore, through multi-module collaboration, even if a module fails, other modules can continue to work, ensuring the overall safety of the electrical system.

[0045] Among them, each ignition signal in T1-Tn provided by the embodiment of the present invention corresponds to a specific pyrotechnic component or battery component, which ensures the accuracy and pertinence of the activation operation and avoids unnecessary risks.

[0046] In some of the embodiments, the above-mentioned aircraft ignition device also includes an onboard power supply monitoring module, a computer module and a bus isolation module; wherein the onboard power supply monitoring module is used to isolate the power supply voltage values ​​corresponding to the onboard power supplies V1-Vm received on the aircraft, and convert the power supply voltage values ​​into output voltage signals U1-Um that share the same ground with the computer module; wherein m is the number of onboard power supplies corresponding to the aircraft; the computer module is used to receive the output voltage signals U1-Um, pack the output voltage signals U1-Um into monitoring information Dq, and send the monitoring information Dq to the bus isolation module; the bus isolation module is used to electrically isolate the received monitoring information Dq to obtain isolated monitoring information Dgq, and send the isolated monitoring information Dgq to the flight management module.

[0047] Among them, On-Board Power Supply refers to the device or system that provides electrical energy to the aircraft and its various subsystems. It can include the main power supply (such as batteries, fuel cells, solar panels, etc.), backup power supply (such as supercapacitors, auxiliary batteries, etc.) and power management system. The on-board power supply can ensure that the aircraft can obtain a stable and reliable power supply during the entire mission, supporting the normal operation of various functions from navigation control to communication telemetry.

[0048] Based on the above configuration, the present invention also provides another aircraft ignition device, such as Figure 2 As shown in the figure, the aircraft ignition device not only includes an ignition control module, an ignition command input detection module and an ignition signal output detection module, but also integrates an onboard power monitoring module, a computer module and a bus isolation module. By introducing the onboard power monitoring module, the computer module and the bus isolation module, the aircraft ignition device realizes more comprehensive power management and monitoring, improves data processing and integration capabilities, and ensures the security and reliability of communication. In addition, this design also enhances the intelligence level, redundancy and fault tolerance of the electrical system, provides a more solid technical guarantee for the safe launch of the aircraft, and can meet the needs of modern aviation and aerospace for high reliability, high performance and high intelligence. The redundancy of the electrical system is increased through the coordinated work of the onboard power monitoring module, the computer module and the bus isolation module. Even if a module fails, other modules can continue to work to ensure the normal operation of the entire system. At the same time, through means such as electrical isolation and data packaging, the risk of single point failure is reduced and the fault tolerance of the system is improved.

[0049] Specifically, the on-board power supply monitoring module can safely receive the power supply voltage values ​​of multiple power supplies V1-Vm on the aircraft through electrical isolation technology (such as optocouplers or isolation transformers), ensuring that the potential difference between different power supplies will not affect the stability of the electrical system. At the same time, the received power supply voltage value is converted into an output voltage signal U1-Um that shares the same ground with the computer module power supply, ensuring the consistency and compatibility of the signal, and facilitating subsequent processing and analysis. The output voltage signal U1-Um is received by the computer module and packaged to form monitoring information Dq, and the packaged monitoring information Dq is sent to the bus isolation module to ensure the security and reliability of data transmission. The received monitoring information Dq is electrically isolated by the bus isolation module to obtain the isolated monitoring information Dgq, preventing the influence of signal interference and noise on communication, and improving the stability and security of communication; the isolated monitoring information Dgq is then sent to the flight management module to ensure that the flight management module can obtain the latest power supply status and other key information in a timely and accurate manner, and make necessary decisions and adjustments. By continuously monitoring the power supply status (represented by the output voltage signal U1-Um) and incorporating it into the monitoring information Dq, the computer module can realize intelligent diagnosis and early warning of the power supply system. For example, abnormal power supply voltage fluctuations may indicate a potential failure, and early warning can help take preventive measures. Real-time monitoring of power status helps optimize power distribution to various components on the aircraft, ensuring that critical tasks (such as ignition operations) have sufficient power support while avoiding unnecessary energy waste.

[0050] In some of the embodiments, the above-mentioned computer module is also used to: receive the ignition instruction detection result Zq sent by the ignition instruction input detection module and the ignition signal detection result Tq sent by the ignition signal output detection module, and pack the ignition instruction detection result Zq, the ignition signal detection result Tq and the output voltage signal U1-Um into the monitoring information Dq.

[0051] Through the above settings, the output voltage signal U1-Um is packaged together with other monitoring results (such as the ignition command detection result Zq and the ignition signal detection result Tq) to form comprehensive monitoring information Dq. This data integration method improves the integrity and availability of the monitoring information.

[0052] According to a specific implementation of the embodiment of the present invention, Figure 3 As shown (it should be noted that Figure 3Only one power supply V1 and an output voltage signal U1 corresponding to the power supply voltage value of the power supply V1 are marked, and the other power supplies and the corresponding output voltage signals are not marked in the figure). The onboard power supply monitoring module can receive the power supply voltage value corresponding to the power supply V1-Vm on the aircraft through the isolation amplifier, and convert the power supply voltage value corresponding to the power supply V1-Vm into the output voltage signal U1-Um that shares the same ground with the computer module according to a preset conversion relationship. The computer module is the control center of the aircraft ignition module, including a microcontroller MCU. The MCU has an integrated analog-to-digital conversion function, which is used to receive the ignition instruction monitoring result Zq, the ignition signal monitoring result Tq and the output voltage signal U1-Um, and package the above information to form monitoring information Dq. The bus isolation module can electrically isolate the monitoring information Dq output by the above computer module to form the isolated monitoring information Dgq. This information is used to send to the flight management module for analysis. The bus isolation module uses CAN communication.

[0053] The aircraft ignition device provided in the embodiment of the present invention can simultaneously collect the ignition command detection result Zq, the ignition signal detection result Tq and the output voltage signal U1-Um, and package the above information into monitoring information Dq and send it to the flight management module for analysis, which can provide more input for the control decision and health management of the aircraft, and improve the intelligence level of aircraft control.

[0054] In some of the embodiments, a temperature sensor is integrated in the computer module, and the temperature sensor is used to obtain temperature information of the aircraft. The computer module is also used to package the temperature information into the monitoring information Dq.

[0055] By integrating temperature sensors, the computer module can monitor temperature changes inside or outside the aircraft in real time. As one of the important environmental parameters, temperature information can help the flight management module better evaluate the status of the aircraft, ensure that it operates within the appropriate temperature range, and avoid malfunctions caused by excessively high or low temperatures.

[0056] Based on the temperature information, on the one hand, the computer module can intelligently adjust the working status of each component of the aircraft to optimize performance and energy efficiency. For example, when the temperature is high, the power of certain high-energy consumption components can be appropriately reduced to prevent overheating; in a low temperature environment, heating measures can be taken to ensure normal operation; by reasonably controlling the temperature, the stress and wear of components caused by temperature fluctuations can be reduced, and the service life of the equipment can be extended. On the other hand, the temperature information is packaged into the monitoring information Dq and sent to the flight management module together with other monitoring results, so that the flight management module can obtain more comprehensive data and make more accurate analysis and decisions.

[0057] In some of the embodiments, an analog-to-digital converter is integrated in the computer module, and the analog-to-digital converter is used to convert a voltage signal received by the computer module into a digital signal.

[0058] In the aircraft ignition device, an analog-to-digital converter (ADC) is integrated in the computer module to convert the received voltage signal (such as the output voltage signal U1-Um, the ignition command detection result Zq and the ignition signal detection result Tq, etc.) into a digital signal. Digital signals have strong anti-interference capabilities and can maintain stable transmission in complex electromagnetic environments, which improves the reliability and stability of the entire aircraft electrical system, especially in application scenarios such as aircraft that have extremely high reliability requirements.

[0059] Through the above settings, the design of integrating analog-to-digital converter (ADC) in the computer module significantly improves the data processing accuracy, electrical system reliability, intelligence level, communication and integration capabilities of the aircraft ignition device. At the same time, it also enhances the security and confidentiality of data, supports remote monitoring and maintenance, and provides a solid technical guarantee for the safe operation of the aircraft.

[0060] In some of the embodiments, an isolation amplifier is integrated in the elastic power supply monitoring module, which receives the power supply voltage values ​​corresponding to the power supplies V1-Vm through the isolation amplifier, and converts the power supply voltage values ​​into output voltage signals U1-Um which are shared with the power supply of the computer module; wherein the amplitude corresponding to the output voltage signal U1-Um is within the analog value acquisition range of the analog-to-digital converter.

[0061] Through the above settings, the isolation amplifier achieves electrical isolation between the input power supply voltage and the output computer module, reducing the safety risks caused by power failure or short circuit, preventing current shocks between different potentials, and protecting sensitive circuits from high voltage or noise. In addition, the isolation amplifier can effectively shield electromagnetic interference (EMI) and other noise sources, maintain signal integrity and accuracy, especially in complex electromagnetic environments or when the input power supply fluctuates greatly, the isolation amplifier can also provide a stable output voltage signal, ensuring the reliability and consistency of subsequent data processing.

[0062] At the same time, since the isolation amplifier can handle a wide range of input voltages, the on-board power monitoring module can adapt to different types of power supplies (such as batteries, generators, etc.), and there is no need to design a specific voltage conversion circuit for each type of power supply, which simplifies the hardware design and manufacturing process, reduces costs, and enhances the versatility and flexibility of the electrical system. The isolation amplifier scales and adjusts the input voltage as needed, so that the amplitude of the output voltage signal U1-Um is within the analog value acquisition range of the analog-to-digital converter (ADC), ensuring the maximum utilization efficiency and accuracy of the signal.

[0063] According to the embodiment of the present invention, the design of integrating the isolation amplifier in the missile power monitoring module makes the missile power monitoring module more compact, which is conducive to miniaturization and integration, and meets the strict requirements of modern aircraft on space and weight. Through electrical isolation and signal conditioning, the need for external wiring is reduced, the system structure is further simplified, and the overall integration is improved.

[0064] The above-mentioned aircraft ignition device provided by the embodiment of the present invention integrates an ignition control module, an ignition instruction input detection module, and an ignition signal output detection module, wherein: the ignition control module is used to receive external ignition instructions Z1-Zn, and generate ignition signals T1-Tn according to the ignition instructions Z1-Zn, so as to respectively activate the corresponding pyrotechnic components or battery components on the aircraft; wherein n is the number of components to be activated on the aircraft; the ignition instruction input detection module is used to receive external ignition instructions Z1-Zn, and output the first electrical The ignition command detection result Zq of the first voltage signal is output, and the ignition command detection result Zq is sent to the telemetry system or integrated measurement system corresponding to the aircraft; wherein, different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition commands Z1-Zn; an ignition signal output detection module is used to receive the ignition signals T1-Tn, output the ignition signal detection result Tq presented as a second voltage signal according to the ignition signals T1-Tn, and send the ignition signal detection result Tq to the telemetry system or integrated measurement system; wherein, different voltage amplitudes in the second voltage signal are used to respectively characterize the output states of the ignition signals T1-Tn. The ignition function is achieved through the ignition control module, and the status of the ignition command and the ignition signal can be detected before the aircraft is launched through the ignition command input detection module and the ignition signal output detection module, thereby satisfying the self-check function before the aircraft is launched, realizing comprehensive monitoring and management of the ignition process, and improving the reliability and safety of the aircraft ignition device during operation. Based on the intelligent monitoring of the aircraft ignition process, the intelligence level of the aircraft ignition operation is improved, achieving the technical effect of further promoting the miniaturization, integration and intelligent development of the aircraft.

[0065] An embodiment of the present invention further provides an aircraft electrical system, comprising any one of the above-mentioned aircraft ignition devices.

[0066] Based on the above-mentioned aircraft ignition device, the reliability, real-time monitoring capability and intelligence level of the aircraft electrical system have been significantly improved. At the same time, the modular design and unified voltage signal standard of the aircraft ignition device also facilitate the integration and maintenance of the aircraft electrical system, providing a solid guarantee for the safe launch of the aircraft.

[0067] The embodiment of the present invention further provides an aircraft ignition method, which is applied to any of the above-mentioned aircraft ignition devices. Figure 4 As shown, the aircraft ignition method 400 provided by the embodiment of the present invention mainly includes:

[0068] Step S401, an ignition control module based on the aircraft ignition device receives external ignition instructions Z1-Zn, and generates ignition signals T1-Tn according to the ignition instructions Z1-Zn to activate the corresponding pyrotechnic components or battery components on the aircraft respectively; wherein n is the number of corresponding components to be activated on the aircraft.

[0069] Through the above settings, the ignition control module automatically generates the corresponding ignition signal according to the received ignition command, and automatically detects and feedbacks, which reduces the need for manual intervention and improves the automation of the aircraft ignition operation. In addition, each ignition signal in T1-Tn corresponds to a specific pyrotechnic component or battery component, ensuring the accuracy and pertinence of the activation operation and avoiding unnecessary risks.

[0070] Step S402, an ignition command input detection module based on the aircraft ignition device receives an external ignition command Z1-Zn, outputs an ignition command detection result Zq presented as a first voltage signal according to the ignition command Z1-Zn, and sends the ignition command detection result Zq to a telemetry system or integrated measurement system corresponding to the aircraft; wherein different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition commands Z1-Zn.

[0071] By detecting the ignition instructions Z1-Zn, it helps to ensure the accuracy of the ignition instruction reception and improve the reliability of the ignition process. The ignition instruction detection result Zq is sent to the telemetry system or comprehensive measurement system in a timely manner, realizing real-time monitoring of the ignition process, facilitating subsequent data analysis and troubleshooting, and also allowing the ground control center to instantly understand the ignition status, respond quickly, and take measures to adjust or terminate the operation when necessary.

[0072] Among them, the different voltage amplitudes in the ignition command detection result Zq presented as a voltage signal are used to characterize the state of the ignition command, making the state information more intuitive and easy to identify, reducing the possibility of misjudgment and enhancing the stability and safety of the aircraft ignition process. Based on the different voltage amplitudes of the first voltage signal, the aircraft electrical system can realize intelligent diagnosis of the ignition command state. For example, an abnormal voltage amplitude may indicate a potential problem, such as a line fault or component failure, which is helpful for early warning and preventive maintenance.

[0073] Step S403, the ignition signal output detection module based on the aircraft ignition device receives the ignition signal T1-Tn, outputs the ignition signal detection result Tq presented as a second voltage signal according to the ignition signal T1-Tn, and sends the ignition signal detection result Tq to the telemetry system or the integrated measurement system; wherein, different voltage amplitudes in the second voltage signal are used to respectively characterize the output states of the ignition signals T1-Tn.

[0074] By detecting the ignition signals T1-Tn, it is helpful to verify the successful generation and transmission of the ignition signal and improve the reliability of the ignition process. The ignition signal detection result Tq is sent to the telemetry system or the comprehensive measurement system in a timely manner, realizing real-time monitoring of the ignition process, facilitating subsequent data analysis and troubleshooting, and also allowing the ground control center to instantly understand the ignition status, respond quickly, and take measures to adjust or terminate the operation when necessary. Among them, the different voltage amplitudes in the ignition signal detection result Tq presented as a voltage signal are used to characterize the state of the ignition signal, which reduces the possibility of misjudgment and enhances the stability and safety of the electrical system. And based on the different voltage amplitudes of the second voltage signal, the aircraft electrical system can realize intelligent diagnosis of the ignition signal state.

[0075] In some of the embodiments, the aircraft ignition device also includes an onboard power supply monitoring module, a computer module and a bus isolation module; the above method also includes: based on the onboard power supply monitoring module, isolating the power supply voltage values ​​corresponding to the onboard power supplies V1-Vm on the aircraft, and converting the power supply voltage values ​​into output voltage signals U1-Um that share the same ground with the computer module; wherein m is the number of onboard power supplies corresponding to the aircraft; based on the computer module, receiving the output voltage signals U1-Um, packaging the output voltage signals U1-Um into monitoring information Dq, and sending the monitoring information Dq to the bus isolation module; based on the bus isolation module, electrically isolating the received monitoring information Dq to obtain isolated monitoring information Dgq, and sending the isolated monitoring information Dgq to the flight management module.

[0076] Based on the above settings, more comprehensive power management and monitoring are achieved, data processing and integration capabilities are improved, and the security and reliability of communication are ensured. By isolating the power supply voltage values ​​received from multiple power supplies V1-Vm on the aircraft, it is ensured that the potential difference between different power supplies will not affect the stability of the electrical system. At the same time, the received power supply voltage value is converted into an output voltage signal U1-Um that shares the same ground with the computer module power supply, ensuring the consistency and compatibility of the signal, which is convenient for subsequent processing and analysis. By packaging the output voltage signal U1-Um to form monitoring information Dq, and sending the packaged monitoring information Dq to the bus isolation module, the security and reliability of data transmission are ensured. By electrically isolating the received monitoring information Dq to obtain the isolated monitoring information Dgq, the influence of signal interference and noise on communication is prevented, and the stability and security of communication are improved; the isolated monitoring information Dgq is then sent to the flight management module to ensure that the flight management module can obtain the latest power supply status and other key information in a timely and accurate manner, and make necessary decisions and adjustments. By continuously monitoring the power supply status (represented by the output voltage signal U1-Um) and incorporating it into the monitoring information Dq, intelligent diagnosis and early warning of the power supply system are achieved.

[0077] In some of the embodiments, the above method also includes: receiving, through a computer module, an ignition command detection result Zq sent by an ignition command input detection module and an ignition signal detection result Tq sent by an ignition signal output detection module, and packaging the ignition command detection result Zq, the ignition signal detection result Tq and the output voltage signal U1-Um into monitoring information Dq.

[0078] Through the above settings, the output voltage signal U1-Um is packaged together with other monitoring results (such as the ignition command detection result Zq and the ignition signal detection result Tq) to form comprehensive monitoring information Dq. This data integration method improves the integrity and availability of the monitoring information.

[0079] In some of the embodiments, a temperature sensor is integrated in the computer module, and the temperature sensor is used to obtain temperature information of the aircraft; the method further includes: packaging the temperature information into the monitoring information Dq through the calculator module.

[0080] Through the above settings, on the one hand, the computer module can be combined with temperature information to intelligently adjust the working state of each component of the aircraft to optimize performance and energy efficiency; by reasonably controlling the temperature, the stress and wear of the components caused by temperature fluctuations can be reduced, and the service life of the equipment can be extended. On the other hand, the temperature information is packaged into the monitoring information Dq and sent to the flight management module together with other monitoring results, so that the flight management module can obtain more comprehensive data and make more accurate analysis and decisions.

[0081] In some of the embodiments, an analog-to-digital converter is integrated in the computer module, and the method further comprises: converting the voltage signal received by the computer module into a digital signal by the analog-to-digital converter.

[0082] Through the above settings, the received voltage signals (such as output voltage signals U1-Um, ignition command detection results Zq and ignition signal detection results Tq, etc.) are converted into digital signals through the analog-to-digital converter in the computer module. Since digital signals have strong anti-interference capabilities, they can maintain stable transmission in complex electromagnetic environments, thereby improving the reliability and stability of the entire aircraft ignition operation.

[0083] In some of the embodiments, an isolation amplifier is integrated in the on-board power supply monitoring module; the above-mentioned steps of isolating the power supply voltage values ​​corresponding to the power supplies V1-Vm on the aircraft based on the on-board power supply monitoring module and converting the power supply voltage values ​​into output voltage signals U1-Um that are shared with the power supply of the computer module include: receiving the power supply voltage values ​​corresponding to the power supplies V1-Vm respectively through the isolation amplifier integrated in the on-board power supply monitoring module, and converting the power supply voltage values ​​into output voltage signals U1-Um that are shared with the power supply of the computer module; wherein the amplitude corresponding to the output voltage signal U1-Um is within the analog value acquisition range of the analog-to-digital converter.

[0084] Through the above settings, electrical isolation between the input power supply voltage and the output computer module is achieved, reducing the safety risks caused by power failure or short circuit, preventing current shocks between different potentials, and protecting sensitive circuits from high voltage or noise. In addition, the isolation amplifier can effectively shield electromagnetic interference (EMI) and other noise sources to maintain signal integrity and accuracy, especially in complex electromagnetic environments or when the input power fluctuates greatly. The isolation amplifier can also provide a stable output voltage signal to ensure the reliability and consistency of subsequent data processing.

[0085] The above-mentioned aircraft ignition method provided by the embodiment of the present invention adopts an ignition control module based on the aircraft ignition device to receive external ignition instructions Z1-Zn, and generates ignition signals T1-Tn according to the ignition instructions Z1-Zn, so as to respectively activate the corresponding pyrotechnic components or battery components on the aircraft; wherein n is the number of components to be activated corresponding to the aircraft; an ignition instruction input detection module based on the aircraft ignition device receives external ignition instructions Z1-Zn, outputs an ignition instruction detection result Zq presented as a first voltage signal according to the ignition instructions Z1-Zn, and sends the ignition instruction detection result Zq to the telemetry system or integrated measurement system corresponding to the aircraft; wherein different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition instructions Z1-Zn; an ignition signal output detection module based on the aircraft ignition device receives An ignition signal T1-Tn is outputted according to the ignition signal T1-Tn, and an ignition signal detection result Tq is presented as a second voltage signal, and the ignition signal detection result Tq is sent to a telemetry system or an integrated measurement system; wherein different voltage amplitudes in the second voltage signal are used to respectively characterize the technical means of the output states of the ignition signal T1-Tn, thereby realizing comprehensive monitoring and management of the ignition process by detecting the states of the ignition command and the ignition signal before the aircraft is launched while satisfying the ignition function, thereby improving the reliability and safety of the aircraft ignition device, significantly improving the reliability, real-time monitoring capability and intelligence level of the aircraft electrical system, and improving the intelligence level of the aircraft ignition operation based on the intelligent monitoring of the aircraft ignition process, thereby achieving the technical effect of further promoting the miniaturization, integration and intelligent development of the aircraft.

[0086] An embodiment of the present invention further provides a non-transitory machine-readable medium storing a computer program, wherein the computer program, when executed by a processor of a computer, is used to cause the computer to execute the method of the embodiment of the present invention.

[0087] The embodiment of the present invention further provides a computer program product, including a computer program, wherein the computer program is used to make the computer perform the method of the embodiment of the present invention when executed by a processor of the computer. The computer program product should be understood as a software product that mainly implements the above method of the present application through a computer program.

[0088] An embodiment of the present invention further provides an electronic device, comprising: at least one processor; and a memory in communication with the at least one processor. The memory stores a computer program executable by the at least one processor, and when the computer program is executed by the at least one processor, the electronic device executes the method of the embodiment of the present invention.

[0089] refer to Figure 5, a block diagram of an electronic device that can be used as a server or client of an embodiment of the present invention will now be described, which is an example of a hardware device that can be applied to various aspects of the present invention. The electronic device is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workbenches, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples and are not intended to limit the implementation of the present invention described and / or required herein.

[0090] like Figure 5 As shown, the electronic device includes a computing unit 501, which can perform various appropriate actions and processes according to a computer program stored in a read-only memory (ROM) 502 or a computer program loaded from a storage unit 508 into a random access memory (RAM) 503. In the RAM 503, various programs and data required for the operation of the electronic device can also be stored. The computing unit 501, the ROM 502, and the RAM 503 are connected to each other via a bus 504. An input / output (I / O) interface 505 is also connected to the bus 504.

[0091] Multiple components in the electronic device are connected to the I / O interface 505, including: an input unit 506, an output unit 507, a storage unit 508, and a communication unit 509. The input unit 506 can be any type of device that can input information to the electronic device, and the input unit 506 can receive input digital or character information, and generate key signal input related to user settings and / or function control of the electronic device. The output unit 507 can be any type of device that can present information, and can include but is not limited to a display, a speaker, a video / audio output terminal, a vibrator, and / or a printer. The storage unit 508 can include but is not limited to a disk, an optical disk. The communication unit 509 allows the electronic device to exchange information / data with other devices through a computer network such as the Internet and / or various telecommunication networks, and can include but is not limited to a modem, a network card, an infrared communication device, and / or a wireless communication transceiver, such as a Bluetooth device, a WiFi device, a WiMax device, a cellular communication device, and / or the like.

[0092] The computing unit 501 may be a variety of general and / or special processing components with processing and computing capabilities. Some examples of the computing unit 501 include, but are not limited to, a CPU, a graphics processing unit (GPU), various dedicated artificial intelligence (AI) computing units, various computing units running machine learning model algorithms, digital signal processors (DSPs), and any appropriate processors, controllers, microcontrollers, etc. The computing unit 501 performs the various methods and processes described above. For example, in some embodiments, the method embodiments of the present invention may be implemented as a computer program, which is tangibly contained in a machine-readable medium, such as a storage unit 508. In some embodiments, part or all of the computer program may be loaded and / or installed on an electronic device via a ROM 502 and / or a communication unit 509. In some embodiments, the computing unit 501 may be configured to perform the above-described method in any other appropriate manner (e.g., by means of firmware).

[0093] The computer programs for implementing the methods of the embodiments of the present invention may be written in any combination of one or more programming languages. These computer programs may be provided to a processor or controller of a general-purpose computer, a special-purpose computer, or other programmable data processing device, so that when the computer programs are executed by the processor or controller, the functions / operations specified in the flow chart and / or block diagram are implemented. The computer programs may be executed entirely on the machine, partially on the machine, partially on the machine as a stand-alone software package and partially on a remote machine, or entirely on a remote machine or server.

[0094] In the context of an embodiment of the present invention, a machine-readable medium may be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, device, or equipment. A machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. A machine-readable signal medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, or infrared systems, devices, or equipment, or any suitable combination of the foregoing. More specific examples of machine-readable storage media may include electrical connections based on one or more lines, portable computer disks, hard disks, random access memories (RAM), read-only memories (ROM), erasable programmable read-only memories (EPROM or flash memory), optical fibers, portable compact disk read-only memories (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the foregoing.

[0095] It should be noted that the term "including" and its variations used in the embodiments of the present invention are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". The modifications of "one" and "multiple" mentioned in the embodiments of the present invention are illustrative rather than restrictive. Those skilled in the art should understand that unless the context clearly indicates otherwise, it should be understood as "one or more".

[0096] The information / data involved in the embodiments of the present invention (including but not limited to data used for analysis, data stored, data displayed, etc.) are all information / data authorized by the user or fully authorized by all parties, and the collection, use and processing of relevant information / data must comply with relevant laws, regulations and standards of relevant countries and regions, and corresponding operation entrances are provided for users to choose to authorize or refuse.

[0097] The various steps described in the method implementation methods provided in the embodiments of the present invention may be performed in different orders and / or in parallel. In addition, the method implementation methods may include additional steps and / or omit the steps shown. The scope of protection of the present invention is not limited in this respect.

[0098] The term "embodiment" in this specification refers to specific features, structures or characteristics described in conjunction with the embodiment that can be included in at least one embodiment of the present invention. The appearance of this phrase in various places in the specification does not necessarily mean the same embodiment, nor does it mean that it is mutually exclusive with other embodiments and is independent or optional. The various embodiments in this specification are described in a related manner, and the same or similar parts between the various embodiments refer to each other. In particular, for the device, equipment, and system embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the relevant parts refer to the partial description of the method embodiment.

[0099] The above-mentioned embodiments only express several implementation methods of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of protection. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present invention, and these all belong to the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the attached claims.

Claims

1. An aircraft ignition device, characterized in that: It includes an ignition control module, an ignition command input detection module, and an ignition signal output detection module, wherein: The ignition control module is used to receive external ignition instructions Z1-Zn, and generate ignition signals T1-Tn according to the ignition instructions Z1-Zn, so as to activate the corresponding pyrotechnic components or battery components on the aircraft respectively; wherein n is the number of components to be activated corresponding to the aircraft; The ignition instruction input detection module is used to receive the external ignition instructions Z1-Zn, output an ignition instruction detection result Zq presented as a first voltage signal according to the ignition instructions Z1-Zn, and send the ignition instruction detection result Zq to the telemetry system or integrated measurement system corresponding to the aircraft; wherein different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition instructions Z1-Zn; The ignition signal output detection module is used to receive the ignition signal T1-Tn, output the ignition signal detection result Tq presented as a second voltage signal according to the ignition signal T1-Tn, and send the ignition signal detection result Tq to the telemetry system or the integrated measurement system; wherein, different voltage amplitudes in the second voltage signal are used to respectively characterize the output states of the ignition signals T1-Tn.

2. The device according to claim 1, characterized in that The device also includes an on-board power supply monitoring module, a computer module and a bus isolation module; wherein, The missile power supply monitoring module is used to isolate and receive the power supply voltage values ​​corresponding to the missile power supplies V1-Vm on the aircraft, and convert the power supply voltage values ​​into output voltage signals U1-Um that share the same ground with the computer module; wherein m is the number of missile power supplies corresponding to the aircraft; The computer module is used to receive the output voltage signal U1-Um, pack the output voltage signal U1-Um into monitoring information Dq, and send the monitoring information Dq to the bus isolation module; The bus isolation module is used to electrically isolate the received monitoring information Dq to obtain isolated monitoring information Dgq, and send the isolated monitoring information Dgq to the flight management module.

3. The device according to claim 2, characterized in that The computer module is also used for: Receive the ignition instruction detection result Zq sent by the ignition instruction input detection module and the ignition signal detection result Tq sent by the ignition signal output detection module, and pack the ignition instruction detection result Zq, the ignition signal detection result Tq and the output voltage signal U1-Um into the monitoring information Dq.

4. The device according to claim 3, characterized in that The computer module is integrated with a temperature sensor, and the temperature sensor is used to obtain the temperature information of the aircraft. The calculator module is also used to pack the temperature information into the monitoring information Dq.

5. The device according to any one of claims 2 to 4, characterized in that: An analog-to-digital converter is integrated in the computer module, and the analog-to-digital converter is used to convert the voltage signal received by the computer module into a digital signal.

6. The device according to claim 5, characterized in that The on-board power supply monitoring module is integrated with an isolation amplifier, and the on-board power supply monitoring module receives the power supply voltage values ​​corresponding to the power supplies V1-Vm respectively through the isolation amplifier, and converts the power supply voltage values ​​into output voltage signals U1-Um that share the same ground as the power supply of the computer module; wherein the amplitude corresponding to the output voltage signal U1-Um is within the analog value acquisition range of the analog-to-digital converter.

7. An aircraft ignition method, characterized in that: The aircraft ignition device applied to any one of claims 1 to 6, the method comprising: The ignition control module based on the aircraft ignition device receives external ignition instructions Z1-Zn, and generates ignition signals T1-Tn according to the ignition instructions Z1-Zn to activate the corresponding pyrotechnic components or battery components on the aircraft respectively; wherein n is the number of components to be activated corresponding to the aircraft; The ignition command input detection module based on the aircraft ignition device receives the external ignition command Z1-Zn, outputs the ignition command detection result Zq presented as a first voltage signal according to the ignition command Z1-Zn, and sends the ignition command detection result Zq to the telemetry system or integrated measurement system corresponding to the aircraft; wherein different voltage amplitudes in the first voltage signal are used to respectively characterize the input states of the ignition commands Z1-Zn; An ignition signal output detection module based on the aircraft ignition device receives the ignition signal T1-Tn, outputs an ignition signal detection result Tq presented as a second voltage signal according to the ignition signal T1-Tn, and sends the ignition signal detection result Tq to the telemetry system or the integrated measurement system; wherein different voltage amplitudes in the second voltage signal are used to respectively characterize the output states of the ignition signals T1-Tn.

8. The method according to claim 7, characterized in that The aircraft ignition device further includes an onboard power supply monitoring module, a computer module and a bus isolation module; the method further includes: Based on the on-board power supply monitoring module, the on-board power supply V1-Vm on the aircraft is isolated and received, and the power supply voltage values ​​are converted into output voltage signals U1-Um that are grounded with the computer module; wherein m is the number of on-board power supplies corresponding to the aircraft; Based on the computer module receiving the output voltage signal U1-Um, the output voltage signal U1-Um is packaged into monitoring information Dq, and the monitoring information Dq is sent to the bus isolation module; Based on the bus isolation module, the received monitoring information Dq is electrically isolated to obtain isolated monitoring information Dgq, and the isolated monitoring information Dgq is sent to the flight management module.

9. An electronic device, comprising: A processor, and a memory storing a program, wherein the program comprises instructions, which, when executed by the processor, cause the processor to perform the method according to any one of claims 7-8.

10. A non-transitory machine-readable medium storing computer instructions, characterized in that: The computer instructions are used to cause the computer to execute the method according to any one of claims 7-8.

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