Emergency guarantee method and system under aircraft auxiliary power fault condition

Abstract

The invention belongs to the technical field of aircraft emergency guarantee, and particularly relates to an emergency guarantee method and system under an aircraft auxiliary power fault condition. The method comprises the following steps: S1, sending a task type, an APU fault code, aircraft model data and aircraft current state data to a ground air source vehicle by an aircraft; s2, starting a corresponding working mode by the ground air source vehicle; s3, performing gas circuit connection and circuit connection between the ground gas source vehicle and the aircraft, and controlling opening and closing of each valve and an actuator in the aircraft by the aircraft according to the connection state information and the working mode of the ground gas source vehicle; and S4, dynamically adjusting gas supply parameters of the ground gas source vehicle according to the collected gas path state data of the ground gas source vehicle and the airplane. According to the invention, rapid information transmission and task cooperation between the airplane and the ground air source vehicle are realized, and the emergency starting response speed is obviously improved.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft emergency support, and in particular relates to an emergency support method and system under the condition of aircraft auxiliary power failure. Background Art

[0002] As a key component of the aircraft, the auxiliary power unit (APU) is responsible for providing compressed air and electricity to the aircraft to ensure the normal start-up of the aircraft and the normal operation of the onboard systems. However, the APU may also fail due to long-term use, environmental conditions, mechanical wear and tear, etc. Generally, for some serious faults, the aircraft needs to be grounded and repaired immediately; for faults that do not affect flight safety, the aircraft is allowed to continue to operate in a "fault retention" mode, in which the aircraft will be emergency started or ground maintained by ground support equipment. Although this method allows the aircraft to continue operating without affecting flight safety and rely on ground support equipment for emergency start-up or maintenance, as ground support equipment is increasingly moving towards high integration, this method has exposed the following significant shortcomings, especially in terms of coordinating aircraft and ground support equipment: 1. Lack of coordination mechanism: There is a lack of efficient and systematic coordination mechanism between aircraft and ground support equipment, which leads to cumbersome connection, communication and collaboration processes, affecting the efficiency of emergency response.

[0003] 2. Poor information transmission: Due to insufficient communication means between aircraft and ground equipment, fault information and operating status are difficult to share in a timely manner, which hinders the realization of efficient collaboration and reduces the effectiveness of emergency support.

[0004] 3. Insufficient intelligence: The level of automation and intelligence is low, and it relies on manual operation, which increases the complexity and risk of operations and slows down the emergency response speed. Summary of the invention

[0005] In order to solve the above technical problems, the present application provides an emergency support method and system under the condition of aircraft auxiliary power failure, so as to improve the coordination efficiency and startup success rate between the ground air source vehicle and the aircraft.

[0006] The first aspect of the present application provides an emergency support method under the condition of aircraft auxiliary power failure, the method mainly comprising: Step S1, the aircraft sends the mission type, APU fault code, aircraft model data and aircraft current status data to the ground air source vehicle; Step S2: The ground gas source vehicle activates the corresponding working mode; Step S3, connecting the ground gas source vehicle to the aircraft through gas circuits and circuits, and the aircraft controls the opening and closing of valves and actuators inside the aircraft according to the connection status information and the working mode of the ground gas source vehicle; Step S4: dynamically adjusting the air supply parameters of the ground air source vehicle according to the collected air path status data of the ground air source vehicle and the aircraft.

[0007] Preferably, in step S1, the task type includes an emergency start-up task or a ground maintenance task.

[0008] Preferably, step S2 further comprises: Step S21, taking the mission type, APU fault code, aircraft model data and aircraft current status data as input, outputting a working mode including air supply parameters based on a pre-trained air supply model; Step S22: start and adjust the gas supply equipment of the ground gas source vehicle according to the working mode.

[0009] Preferably, in step S4, the air path status data of the ground air source vehicle and the aircraft are collected by means of a pressure sensor, a flow meter and a temperature sensor.

[0010] Preferably, the method further comprises: When the collected gas path status data exceeds the threshold, an alarm is issued.

[0011] The second aspect of the present application provides an emergency support system under the condition of aircraft auxiliary power failure, mainly comprising: Mission information transmission module, used for sending mission type, APU fault code, aircraft model data and aircraft current status data from the aircraft to the ground gas source vehicle; A working mode selection module is used to enable the corresponding working mode by the ground gas source vehicle; The air circuit control module is used to connect the air circuit and circuit between the ground air source vehicle and the aircraft. The aircraft controls the opening and closing of valves and actuators inside the aircraft according to the connection status information and the working mode of the ground air source vehicle. The parameter adjustment module is used to dynamically adjust the air supply parameters of the ground air source vehicle according to the collected air path status data of the ground air source vehicle and the aircraft.

[0012] Preferably, the task type includes an emergency start-up task or a ground maintenance task.

[0013] Preferably, the working mode selection module further includes: A mission analysis unit, which is used to take the mission type, APU fault code, aircraft model data and aircraft current status data as input, and output a working mode including air supply parameters based on a pre-trained air supply model; The air supply control unit is used to start and adjust the air supply equipment of the ground air source vehicle according to the working mode.

[0014] Preferably, in the parameter adjustment module, the gas path status data of the ground gas source vehicle and the aircraft are collected by means of a pressure sensor, a flow meter and a temperature sensor.

[0015] Preferably, the system further comprises: The early warning module is used to issue an alarm when the collected gas path status data exceeds the threshold.

[0016] The present application realizes rapid information transmission and task collaboration between the aircraft and the ground gas source vehicle, significantly improving the emergency start-up response speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a flow chart of a preferred embodiment of the emergency support method under the condition of aircraft auxiliary power failure in the present application.

[0018] Figure 2 This application Figure 1 A schematic diagram of the ground gas source vehicle and aircraft pipeline and actuator control of the illustrated embodiment. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0020] The first aspect of the present application provides an emergency support method under the condition of aircraft auxiliary power failure, such as Figure 1 As shown, the method mainly includes: Step S1, the aircraft sends the mission type, APU fault code, aircraft model data and aircraft current status data to the ground air source vehicle; Step S2: The ground gas source vehicle activates the corresponding working mode; Step S3, connecting the ground gas source vehicle to the aircraft through gas circuits and circuits, and the aircraft controls the opening and closing of valves and actuators inside the aircraft according to the connection status information and the working mode of the ground gas source vehicle; Step S4: dynamically adjusting the air supply parameters of the ground air source vehicle according to the collected air path status data of the ground air source vehicle and the aircraft.

[0021] The present application realizes rapid information transmission and task collaboration between the aircraft and the ground gas source vehicle through the above steps, significantly improving the emergency startup response speed.

[0022] After the APU of the aircraft fails, the present application first sends the mission parameters and status parameters of the aircraft to the ground gas source vehicle in step S1. These parameters include information such as aircraft model, mission type, failure type of APU and priority of the mission, providing accurate mission background and requirements for the ground gas source vehicle, ensuring that the support work can be started quickly and carried out efficiently. In step S2, the ground gas source vehicle conducts a comprehensive analysis of the data transmitted by the aircraft, gives the gas supply parameters, and determines the working mode. After that, in step S3, the gas circuit connection and circuit connection between the ground gas source vehicle and the aircraft are carried out to replace the APU work, and accordingly, the aircraft performs the opening and closing control of each valve and actuator. In this process, the ground gas source vehicle and the aircraft connection status information, the aircraft gas circuit status information, and the gas supply status information of the gas source vehicle are mutually transmitted between the ground gas source vehicle and the aircraft to ensure task synchronization and instruction execution. In step S4, the gas circuit parameters are collected by sensors to dynamically adjust the gas supply parameters.

[0023] In some optional implementations, in step S1, the task type includes an emergency startup task or a ground maintenance task.

[0024] It is understandable that different mission types correspond to different ground air source vehicle working modes, and the control strategies of the aircraft's valves and actuators are also different. For example, when the aircraft performs an emergency start mission, the emergency start working mode is selected in step S2, the air compressor starts working, and the main air supply pipeline pressure increases to 35-42psi. Figure 2 In step S3, the aircraft controls the air conditioning system bleed valve to close, the one-way bleed valve of the separated air pressure type auxiliary power air pipeline to open, the engine disconnection mechanism to close, and the ground air source vehicle controls the flow control valve to provide 35-40psi air to the aircraft after receiving the aircraft's confirmation status. When the aircraft performs a long-term low-power ground maintenance task, the low-power ground maintenance task working mode is selected in step S2, and the air compressor starts working. The pipeline pressure increases to 25-30psi. In step S3, the aircraft controls the air conditioning system bleed valve to open, the one-way valve of the separated air pressure type auxiliary power air pipeline to open, and the engine disconnection mechanism to open. After receiving the aircraft's confirmation status, the ground air source vehicle controls the flow control valve to provide 25-30psi air to the aircraft.

[0025] In some optional implementations, step S2 further includes: Step S21, taking the mission type, APU fault code, aircraft model data and aircraft current status data as input, outputting a working mode including air supply parameters based on a pre-trained air supply model; Step S22: start and adjust the gas supply equipment of the ground gas source vehicle according to the working mode.

[0026] In this embodiment, the ground air source vehicle matches the optimal air supply solution through the pre-trained air supply model according to the actual fault condition of the APU. The air supply model outputs the decision result by comprehensively analyzing the current state of the aircraft, mission requirements and environmental conditions, and then starts and adjusts the air supply equipment of the air source vehicle in step S22 to ensure that the air supply parameters match the aircraft requirements. The air supply equipment of the air source vehicle should be able to dynamically adjust the air supply pressure, temperature and flow rate to meet the aircraft's requirements for different emergency support tasks.

[0027] The air supply model may adopt a BP neural network, for example, and perform supervised training through the relationship between historical fault data and corresponding air supply parameters. The input layer nodes correspond to features such as task type, APU fault code, etc., and the output layer is the working mode.

[0028] In step S3, the valves inside the aircraft mainly refer to the input and output bleed air valves of the aircraft auxiliary power air pipeline and the bleed air valve of the air conditioning system, and the actuators inside the aircraft mainly refer to the accessory casing disengagement mechanism.

[0029] In step S4, real-time operating data of the air supply equipment and the aircraft air path are collected through a variety of high-precision sensors, and then the feedback control algorithm is used to adjust the output parameters according to the real-time collected air supply data to ensure the stability of the air supply process.

[0030] In some optional implementations, in step S4, the gas path status data of the ground gas source vehicle and the aircraft are collected through pressure sensors, flow meters and temperature sensors.

[0031] In some optional embodiments, the method further comprises: When the collected gas path status data exceeds the threshold, an alarm is issued.

[0032] This application uses sensors to monitor airflow status, environmental parameters and other information in real time, and transmits the monitoring data to the control platform for ground maintenance personnel to view. If an abnormal state is detected, an alarm is processed. In an alternative implementation, the aircraft's operating data is also monitored, and an alarm signal is triggered when the air path status data and operating parameters exceed the threshold, reminding the operator to intervene. Through a multi-level alarm mechanism, visual, sound or communication alarm signals can be triggered according to the degree of excess.

[0033] During ground maintenance tasks, this application can complete the air supply operation without starting the aircraft engine, effectively saving fuel consumption and extending the service life of the aircraft. Under extreme temperature conditions, this application can achieve dynamic adjustment of the cabin environment through the temperature control function to ensure operational efficiency and equipment safety. This application avoids startup failures caused by extreme weather such as strong winds, and ensures the stability of the air supply and startup process. This application uses sensor data and dynamic feedback mechanisms to control the operating status of the air supply equipment in real time and respond quickly to abnormalities, reducing safety risks.

[0034] The second aspect of the present application provides an emergency support system under the condition of aircraft auxiliary power failure corresponding to the above method, mainly comprising: Mission information transmission module, used for sending mission type, APU fault code, aircraft model data and aircraft current status data from the aircraft to the ground gas source vehicle; A working mode selection module is used to enable the corresponding working mode by the ground gas source vehicle; The air circuit control module is used to connect the air circuit and circuit between the ground air source vehicle and the aircraft. The aircraft controls the opening and closing of valves and actuators inside the aircraft according to the connection status information and the working mode of the ground air source vehicle. The parameter adjustment module is used to dynamically adjust the air supply parameters of the ground air source vehicle according to the collected air path status data of the ground air source vehicle and the aircraft.

[0035] In some optional implementations, the task type includes an emergency startup task or a ground maintenance task.

[0036] In some optional implementations, the working mode selection module further includes: A mission analysis unit, which is used to take the mission type, APU fault code, aircraft model data and aircraft current status data as input, and output a working mode including air supply parameters based on a pre-trained air supply model; The air supply control unit is used to start and adjust the air supply equipment of the ground air source vehicle according to the working mode.

[0037] In some optional implementations, in the parameter adjustment module, the gas path status data of the ground gas source vehicle and the aircraft are collected through pressure sensors, flow meters and temperature sensors.

[0038] In some optional embodiments, the system further comprises: The early warning module is used to issue an alarm when the collected gas path status data exceeds the threshold.

[0039] The above is only a specific implementation of the present application, but the protection scope of the present application 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 application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An emergency support method under the condition of aircraft auxiliary power failure, characterized in that: The method comprises: Step S1, the aircraft sends the mission type, APU fault code, aircraft model data and aircraft current status data to the ground air source vehicle; Step S2: The ground gas source vehicle activates the corresponding working mode; Step S3, connecting the ground gas source vehicle to the aircraft through gas circuits and circuits, and the aircraft controls the opening and closing of valves and actuators inside the aircraft according to the connection status information and the working mode of the ground gas source vehicle; Step S4: dynamically adjusting the air supply parameters of the ground air source vehicle according to the collected air path status data of the ground air source vehicle and the aircraft.

2. The emergency support method under the condition of aircraft auxiliary power failure according to claim 1, characterized in that: In step S1, the task type includes an emergency start-up task or a ground maintenance task.

3. The emergency support method under the condition of aircraft auxiliary power failure as claimed in claim 1, characterized in that: Step S2 further comprises: Step S21, taking the mission type, APU fault code, aircraft model data and aircraft current status data as input, outputting a working mode including air supply parameters based on a pre-trained air supply model; Step S22: start and adjust the gas supply equipment of the ground gas source vehicle according to the working mode.

4. The emergency support method under the condition of aircraft auxiliary power failure as claimed in claim 1, characterized in that: In step S4, the air path status data of the ground air source vehicle and the aircraft are collected through pressure sensors, flow meters and temperature sensors.

5. The emergency support method under the condition of aircraft auxiliary power failure as claimed in claim 1, characterized in that: The method further comprises: When the collected gas path status data exceeds the threshold, an alarm is issued.

6. An emergency support system for aircraft auxiliary power failure, characterized in that: include: Mission information transmission module, used for sending mission type, APU fault code, aircraft model data and aircraft current status data from the aircraft to the ground gas source vehicle; A working mode selection module is used to enable the corresponding working mode by the ground gas source vehicle; The air circuit control module is used to connect the air circuit and circuit between the ground air source vehicle and the aircraft. The aircraft controls the opening and closing of valves and actuators inside the aircraft according to the connection status information and the working mode of the ground air source vehicle. The parameter adjustment module is used to dynamically adjust the air supply parameters of the ground air source vehicle according to the collected air path status data of the ground air source vehicle and the aircraft.

7. The emergency support system for aircraft auxiliary power failure as claimed in claim 6, characterized in that: The task types include emergency start-up tasks or ground maintenance tasks.

8. The emergency support system for aircraft auxiliary power failure as claimed in claim 6, characterized in that: The working mode selection module further includes: A mission analysis unit, which is used to take the mission type, APU fault code, aircraft model data and aircraft current status data as input, and output a working mode including air supply parameters based on a pre-trained air supply model; The air supply control unit is used to start and adjust the air supply equipment of the ground air source vehicle according to the working mode.

9. The emergency support system for aircraft auxiliary power failure as claimed in claim 6, characterized in that: In the parameter adjustment module, the gas path status data of the ground gas source vehicle and the aircraft are collected through pressure sensors, flow meters and temperature sensors.

10. The emergency support system for aircraft auxiliary power failure according to claim 6, characterized in that: The system further comprises: The early warning module is used to issue an alarm when the collected gas path status data exceeds the threshold.

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