An emergency support method and system under aircraft auxiliary power failure conditions

Abstract

The present application belongs to the field of aircraft emergency support technology, and particularly relates to an emergency support method and system under aircraft auxiliary power failure conditions. The method comprises: step S1, the aircraft sends the task type, APU fault code, aircraft model data and aircraft current status data to the ground air source vehicle; step S2, the ground air source vehicle activates the corresponding working mode; step S3, the ground air source vehicle and the aircraft are connected in the air circuit and circuit, and the aircraft controls the opening and closing of each valve and actuator inside the aircraft according to the connection status information and the working mode of the ground air source vehicle; step S4, the air supply parameters of the ground air source vehicle are dynamically adjusted according to the collected air circuit status data of the ground air source vehicle and the aircraft. The present application realizes the rapid information transmission and task collaboration between the aircraft and the ground air source vehicle, and significantly improves the emergency startup response speed.

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 aircraft auxiliary power failure conditions. Background Art

[0002] As a key component of an aircraft, the auxiliary power unit (APU) is responsible for providing compressed air and electricity to the aircraft, ensuring the normal start-up of the aircraft and the normal operation of the onboard systems. However, the APU may also fail due to factors such as long-term use, environmental conditions and mechanical wear. Generally speaking, for certain serious faults, the aircraft needs to be grounded immediately and repaired; for faults that do not affect flight safety, the aircraft is allowed to continue operating in a "fault retention" mode. In this mode, the aircraft will be emergency started or maintained on the ground through 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:

[0003] 1. Lack of coordination mechanism: There is a lack of efficient and systematic coordination mechanism between aircraft and ground support equipment, resulting in cumbersome connection, communication and collaboration processes, which affects the efficiency of emergency response.

[0004] 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.

[0005] 3. Insufficient intelligence: The level of automation and intelligence is low, and it relies on manual operation, which increases operational complexity and risks and slows down emergency response speed. Summary of the Invention

[0006] 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, which improves the coordination efficiency and startup success rate between the ground air source vehicle and the aircraft.

[0007] In a first aspect, the present application provides an emergency support method for an aircraft auxiliary power failure, the method mainly comprising:

[0008] 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;

[0009] Step S2: The ground gas source vehicle activates the corresponding working mode;

[0010] Step S3: Connect the air circuits and circuits between the ground air source vehicle and the aircraft, and the aircraft controls the opening and closing of valves and actuators inside the aircraft based on the connection status information and the working mode of the ground air source vehicle.

[0011] 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.

[0012] Preferably, in step S1, the task type includes an emergency start-up task or a ground maintenance task.

[0013] Preferably, step S2 further comprises:

[0014] Step S21: Taking the mission type, APU fault code, aircraft model data, and aircraft current status data as input, output an operating mode including air supply parameters based on a pre-trained air supply model;

[0015] Step S22: Start and adjust the gas supply equipment of the ground gas source vehicle according to the working mode.

[0016] 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.

[0017] Preferably, the method further comprises:

[0018] When the collected gas path status data exceeds the threshold, an alarm is issued.

[0019] The second aspect of the present application provides an emergency support system for aircraft auxiliary power failure, mainly comprising:

[0020] 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 air source vehicle;

[0021] Working mode selection module, used to enable corresponding working mode by ground gas source vehicle;

[0022] 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 based on the connection status information and the working mode of the ground air source vehicle.

[0023] 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.

[0024] Preferably, the task type includes an emergency start-up task or a ground maintenance task.

[0025] Preferably, the working mode selection module further includes:

[0026] The mission analysis unit is used to take the mission type, APU fault code, aircraft model data and aircraft current status data as input, and output the working mode including air supply parameters based on the pre-trained air supply model;

[0027] 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.

[0028] Preferably, 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.

[0029] Preferably, the system further comprises:

[0030] The early warning module is used to issue an alarm when the collected gas path status data exceeds the threshold.

[0031] This application realizes rapid information transmission and task collaboration between aircraft and ground gas source vehicles, significantly improving the emergency startup response speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a flow chart of a preferred embodiment of the emergency support method under the condition of aircraft auxiliary power failure of the present application.

[0033] Figure 2 This application Figure 1 Schematic diagram of the ground air source vehicle, aircraft pipelines and actuator control in the illustrated embodiment. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers 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 should not 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 conjunction with the drawings.

[0035] 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:

[0036] 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;

[0037] Step S2: The ground gas source vehicle activates the corresponding working mode;

[0038] Step S3: Connect the air circuits and circuits between the ground air source vehicle and the aircraft, and the aircraft controls the opening and closing of valves and actuators inside the aircraft based on the connection status information and the working mode of the ground air source vehicle.

[0039] 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.

[0040] Through the above steps, this application realizes rapid information transmission and task collaboration between the aircraft and the ground gas source vehicle, significantly improving the emergency startup response speed.

[0041] After the aircraft APU fails, the present application first sends the aircraft's mission parameters and status parameters to the ground gas source vehicle in step S1. These parameters include information such as aircraft model, mission type, APU failure type, and mission priority, providing the ground gas source vehicle with accurate mission background and requirements, 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 from the aircraft, provides air supply parameters, and determines the working mode. Thereafter, in step S3, the ground gas source vehicle is connected to the aircraft through air circuits and circuits to replace the APU work. Accordingly, the aircraft performs opening and closing control of various valves and actuators. In this process, the ground gas source vehicle and aircraft connection status information, the aircraft air circuit status information, and the air supply status information of the air 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 air circuit parameters are collected by sensors to dynamically adjust the air supply parameters.

[0042] In some optional implementations, in step S1, the task type includes an emergency startup task or a ground maintenance task.

[0043] 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 2In step S3, the aircraft controls the air conditioning system bleed valve to close, the one-way bleed valve on the separate pneumatic pressure-type auxiliary power air line to open, and the engine disconnect mechanism to close. After receiving confirmation from the aircraft, the ground air supply vehicle controls the flow control valve to supply air to the aircraft at a pressure of 35-40 psi. When the aircraft is performing a long-term, low-power ground maintenance mission, the low-power ground maintenance mission operating mode is selected in step S2. The air compressor begins operating, raising the pipeline pressure to 25-30 psi. In step S3, the aircraft controls the air conditioning system bleed valve to open, the one-way valve on the separate pneumatic pressure-type auxiliary power air line to open, and the engine disconnect mechanism to open. After receiving confirmation from the aircraft, the ground air supply vehicle controls the flow control valve to supply air to the aircraft at a pressure of 25-30 psi.

[0044] In some optional embodiments, step S2 further includes:

[0045] Step S21: Taking the mission type, APU fault code, aircraft model data, and aircraft current status data as input, output an operating mode including air supply parameters based on a pre-trained air supply model;

[0046] Step S22: Start and adjust the gas supply equipment of the ground gas source vehicle according to the working mode.

[0047] In this embodiment, the ground-based air supply vehicle uses a pre-trained air supply model to match the optimal air supply solution based on the actual APU failure. The air supply model comprehensively analyzes the aircraft's current state, mission requirements, and environmental conditions to output a decision. Step S22 then activates and adjusts the air supply equipment on the vehicle to ensure that the air supply parameters match the aircraft's requirements. The vehicle's air supply equipment should be able to dynamically adjust the air supply pressure, temperature, and flow rate to meet the aircraft's various emergency support missions.

[0048] 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 and APU fault code, and the output layer is the working mode.

[0049] 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.

[0050] 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. Then, a feedback control algorithm is used to adjust the output parameters based on the real-time collected air supply data to ensure the smoothness of the air supply process.

[0051] 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.

[0052] In some optional embodiments, the method further comprises:

[0053] When the collected gas path status data exceeds the threshold, an alarm is issued.

[0054] This application uses sensors to monitor airflow status, environmental parameters, and other information in real time, and transmits the monitoring data to a control platform for review by ground maintenance personnel. If an abnormal state is detected, an alarm is triggered. In an alternative embodiment, the aircraft's operating data is monitored, and an alarm signal is triggered when the air path status data and operating parameters exceed the threshold, prompting the operator to intervene. A multi-level alarm mechanism can trigger visual, audible, or communication alarm signals based on the degree of the limit violation.

[0055] During ground maintenance tasks, this application can complete air supply operations without starting the aircraft engine, effectively saving fuel consumption and extending the aircraft's service life. Under extreme temperature conditions, this application can dynamically adjust the cabin environment through temperature control functions 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 a dynamic feedback mechanism to monitor the operating status of air supply equipment in real time and quickly respond to anomalies, reducing safety risks.

[0056] A second aspect of the present application provides an emergency support system for aircraft auxiliary power failure corresponding to the above method, mainly comprising:

[0057] 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 air source vehicle;

[0058] Working mode selection module, used to enable corresponding working mode by ground gas source vehicle;

[0059] 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 based on the connection status information and the working mode of the ground air source vehicle.

[0060] 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.

[0061] In some optional implementations, the task type includes an emergency startup task or a ground maintenance task.

[0062] In some optional implementations, the operating mode selection module further includes:

[0063] The mission analysis unit is used to take the mission type, APU fault code, aircraft model data and aircraft current status data as input, and output the working mode including air supply parameters based on the pre-trained air supply model;

[0064] 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.

[0065] 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.

[0066] In some optional embodiments, the system further comprises:

[0067] The early warning module is used to issue an alarm when the collected gas path status data exceeds the threshold.

[0068] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. An emergency support method for 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: Connect the air circuits and circuits between the ground air source vehicle and the aircraft, and the aircraft controls the opening and closing of valves and actuators inside the aircraft based on the connection status information and the working mode of the ground air 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 according to 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, output an operating 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 according to 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 according to 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 air source vehicle; Working mode selection module, used to enable corresponding working mode by 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 based on 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 according to claim 6, characterized in that: The task type includes an emergency startup task or a ground maintenance task.

8. The emergency support system for aircraft auxiliary power failure according to claim 6, characterized in that: The working mode selection module further includes: The mission analysis unit is used to take the mission type, APU fault code, aircraft model data and aircraft current status data as input, and output the working mode including air supply parameters based on the 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 according to 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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