An eVTOL aircraft-based fault simulation design system and method

Abstract

The application discloses a kind of based on eVTOL aircraft's fault simulation design system and method, belong to aircraft fault simulation technical field, specifically include: obtaining the fault data of different types eVOTL aircraft, according to the fault data of pre-set fault classification standard is classified, and establish unified fault model library;Any type eVTOL aircraft core subsystem is simulated by Simulink modeling, from fault model library, in turn, the different fault data of same fault type is extracted, and the fault data is injected into any aircraft simulation system, obtains unified aircraft simulation system fault instruction, in turn, all fault instructions are brought into the aircraft simulation system and are simulated for fault, obtains eVTOL aircraft fault simulation design system.The application is simulated by unified fault simulation design system, reduces pilot fault training cost and improves training efficiency.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft fault simulation, in particular to a fault simulation design system and method based on an eVTOL aircraft. BACKGROUND

[0002] An eVTOL (electric Vertical Take-Off and Landing) aircraft uses electricity to hover, take off and land vertically. As a safe, sustainable, affordable and accessible form of aviation for local tasks, eVTOL mainly serves urban areas and extends to the outskirts of metropolises. It is widely used, and new technologies and business models are driving the transformation of the aviation industry, making aviation play an indispensable role in regional and local transportation.

[0003] In order to ensure the safety of flight, simulation and training equipment is an essential part, which can not only improve the reliability of the aircraft, but also bears the important responsibility of training pilots. The current mainstream development direction is that before the aircraft realizes complete autonomy, pilots are still an important part of ensuring flight safety. The current flight training equipment is designed and operated based on the flight model, that is, a separate development is needed for a specific flight model, and pilots need to be trained differently for different flight models, resulting in a large time cost and low actual training efficiency.

[0004] Unlike the traditional flight training industry, eVTOL technology is relatively new, and there are many designs of eVTOL aircraft. There are currently hundreds of eVTOL aircraft in existence or under development, and the configuration types are diverse, with significant differences between different aircraft. If the traditional training mode is adopted, that is, the training equipment is specific to the aircraft model, it will result in high training costs and low efficiency, which is not conducive to the rapid development of eVOTL aircraft and hinders the commercial progress of eVOTL aircraft. Therefore, a unified eVOTL aircraft fault simulation system is needed to meet the training needs of eVOTL aircraft for faults. SUMMARY

[0005] The purpose of the present application is to provide a fault simulation design system and method based on an eVTOL aircraft, which solves the following technical problems:

[0006] Traditional aircraft training mode is high in cost and low in efficiency, which is not suitable for eVOTL aircraft training, hinders the rapid development of eVOTL aircraft, and therefore a unified eVOTL aircraft fault simulation system is needed to meet the training needs of eVOTL aircraft for faults, so a unified eVOTL aircraft fault simulation system is needed to realize the training of multiple models of training equipment.

[0007] The object of the application can be achieved by the following technical solutions:

[0008] A fault simulation design method based on eVTOL aircraft, comprising the following steps:

[0009] S1, obtain fault data of different types of eVOTL aircraft, classify the fault data according to a preset fault classification standard, and establish a unified fault model library; the fault classification standard is battery system fault, electric drive system fault and flight control system fault;

[0010] S2, modeling and simulation of any type of eVTOL aircraft core subsystem through Simulink, obtaining several types of eVTOL aircraft simulation system, the aircraft simulation system includes power system simulation module, power system simulation module, flight simulation module, display system simulation module, instrument system simulation module, communication system simulation module, sound system simulation module and visual system simulation module;

[0011] S3, different fault data of the same fault type are extracted from the fault model library in sequence, and the fault data are injected into any aircraft simulation system to obtain unified aircraft simulation system fault instruction, all fault instructions are sequentially brought into the aircraft simulation system for fault simulation to obtain eVTOL aircraft fault simulation design system.

[0012] As a further scheme of the application: in S1, the fault data includes battery system data, electric drive system data, flight attitude data navigation and positioning data, communication and connection system data and sensor data.

[0013] As a further scheme of the application: in S3, the specific process of fault data injection is:

[0014] Obtain the fault data corresponding to any simulation module, obtain the circuit netlist corresponding to any fault data, add the fault parameters corresponding to the fault data to the circuit netlist to generate a fault circuit netlist, generate a control command file according to a preset fault duration T and the fault circuit netlist, run the control command file to obtain an actual fault duration t, if the actual fault duration t is located in the interval [T-a, T+a], generate a fault simulation instruction according to the control command file, if the actual fault duration t is located outside the interval [T-a, T+a], increase the fault injection times according to the current actual fault duration and generate a corresponding control command file, and generate a fault simulation instruction according to the control command file.

[0015] As a further scheme of the present application, in the S3, the process of fault simulation is:

[0016] According to the fault command, the simulation module corresponding to the fault command is controlled to run the fault circuit netlist, and real-time data interaction is performed with the remaining simulation modules, so that the display system simulation module displays unit fault warning information, the sound system simulation module broadcasts the warning sound corresponding to the fault, and the visual system simulation module performs visual display corresponding to the fault.

[0017] As a further scheme of the present application, the specific process of data interaction is:

[0018] Preset operation data before the fault command is obtained, the power simulation module calculates the engine thrust according to the preset operation data; the flight simulation module receives the thrust information of the engine system to calculate the aircraft state and flight state; the visual system simulation module generates flight images in real time by computer according to the aircraft state and flight state and transmits them to the display system simulation module; the display system simulation module is used for real-time display of the flight images; the power supply system simulation module calculates the power loss according to the engine thrust;

[0019] The sound system simulation module provides abnormal warning information.

[0020] A fault simulation design system based on an eVTOL aircraft, characterized by comprising:

[0021] A data acquisition module is configured to acquire fault data of different types of eVOTL aircrafts, classify the fault data according to a preset fault classification standard, and establish a unified fault model library; the fault classification standard includes battery system fault, electric drive system fault, and flight control system fault.

[0022] A model simulation module is configured to model and simulate any type of eVTOL aircraft core subsystem through Simulink to obtain several types of eVTOL aircraft simulation systems, wherein the aircraft simulation system comprises a power supply system simulation module, a power system simulation module, a flight simulation module, a display system simulation module, an instrument system simulation module, a communication system simulation module, a sound system simulation module and a visual system simulation module.

[0023] A result generation module is configured to sequentially extract different fault data of the same fault type from the fault model library, and inject the fault data into any aircraft simulation system to obtain unified aircraft simulation system fault instructions, sequentially bring all fault instructions into the aircraft simulation system for fault simulation, and obtain an eVTOL aircraft fault simulation design system.

[0024] The present application has the following advantages:

[0025] The present application obtains fault data of different types of eVOTL aircraft, classifies the fault data according to a preset fault classification standard, establishes a unified fault model library, respectively models and simulates eVTOL aircraft core subsystems to obtain each simulation submodule, sequentially extracts different fault data of the same fault type from the fault model library, and injects the fault data into any aircraft simulation system to obtain unified aircraft simulation system fault instructions, sequentially brings all fault instructions into the aircraft simulation system for fault simulation, and obtains an eVTOL aircraft fault simulation design system. By establishing a unified fault model library and an aircraft simulation system, the fault simulation of different types of eVTOL aircraft is realized on a unified platform, and the pilot fault training cost is reduced and the training efficiency is improved through the unified fault simulation design system. BRIEF DESCRIPTION OF DRAWINGS

[0026] The present application will be further described below with reference to the accompanying drawings.

[0027] Figure 1 is a fault simulation design method flowchart based on an eVTOL aircraft. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0029] Please refer to Figure 1As shown, the application is a fault simulation design method based on eVTOL aircraft, comprising the following steps:

[0030] S1, obtain fault data of different types of eVOTL aircraft, classify the fault data according to the preset fault classification standard, and establish a unified fault model library; the fault classification standard is battery system fault, electric drive system fault and flight control system fault;

[0031] S2, modeling and simulation of any type of eVTOL aircraft core subsystem through Simulink, obtaining several types of eVTOL aircraft simulation system, the aircraft simulation system includes power system simulation module, power system simulation module, flight simulation module, display system simulation module, instrument system simulation module, communication system simulation module, sound system simulation module and visual system simulation module;

[0032] S3, different fault data of the same fault type is extracted from the fault model library in sequence, and the fault data is injected into any aircraft simulation system to obtain a unified aircraft simulation system fault instruction, all fault instructions are sequentially brought into the aircraft simulation system for fault simulation to obtain an eVTOL aircraft fault simulation design system.

[0033] The application obtains fault data of different types of eVOTL aircraft, classifies the fault data according to the preset fault classification standard, and establishes a unified fault model library, then respectively models and simulates the core subsystem of eVTOL aircraft to obtain each simulation submodule, extracts different fault data of the same fault type from the fault model library in sequence, obtains aircraft simulation system fault instruction through fault injection method, sequentially brings all fault instructions into the aircraft simulation system for fault simulation to obtain an eVTOL aircraft fault simulation design system, through establishing a unified fault model library and aircraft simulation system, the fault simulation of different types of eVTOL aircraft is realized on a unified platform, through the unified fault simulation design system, the pilot fault training cost is reduced, and the training efficiency is improved.

[0034] In a preferred embodiment of the application, in S1, the fault data includes battery system data, electric drive system data, flight attitude data navigation and positioning data, communication and connection system data and sensor data.

[0035] In a preferred embodiment of the application, in S3, the specific process of fault data injection is:

[0036] Obtaining fault data corresponding to any simulation module, obtaining a circuit netlist corresponding to any fault data, adding fault parameters corresponding to the fault data to the circuit netlist to generate a fault circuit netlist, generating a control command file according to a preset fault duration T and the fault circuit netlist, running the control command file to obtain an actual fault duration t, if the actual fault duration t is located in the interval [T-a, T+a], generating a fault simulation instruction according to the control command file, if the actual fault duration t is located outside the interval [T-a, T+a], increasing the fault injection times according to the current actual fault duration and generating a corresponding control command file, and generating a fault simulation instruction according to the control command file.

[0037] By combining the fault data with the circuit netlist of the corresponding simulation module, accurate simulation of the fault is realized, ensuring that the simulation system can accurately simulate various fault conditions that the real aircraft may encounter and add fault parameters to the circuit netlist to generate a fault circuit netlist, and the fault circuit netlist is run through the control program written based on C++, realizing automatic fault simulation.

[0038] In a preferred embodiment of the present application, the process of fault simulation in S3 is:

[0039] According to the fault command, the simulation module corresponding to the fault command runs the fault circuit netlist and interacts with the remaining simulation modules in real time, so that the display system simulation module displays the crew fault warning information, the sound system simulation module broadcasts the warning sound corresponding to the fault, and the visual system simulation module displays the visual display corresponding to the fault.

[0040] In a preferred embodiment of the present application, the specific process of data interaction is:

[0041] Obtaining preset operation data before the fault command, the power simulation module calculates the engine thrust according to the preset operation data; the flight simulation module receives the thrust information of the engine system to calculate the aircraft state and flight state; the visual system simulation generates flight images in real time according to the aircraft state and flight state and transmits them to the display system simulation module; the display system simulation module is used for real-time display of the flight images; the power supply system simulation module calculates the power loss according to the engine thrust;

[0042] The sound system simulation module provides abnormal warning information.

[0043] A fault simulation design system based on an eVTOL aircraft, characterized in that it comprises:

[0044] The data acquisition module is used for acquiring fault data of different types of eVOTL aircraft, classifying the fault data according to a preset fault classification standard, and establishing a unified fault model library; the fault classification standard is battery system fault, electric drive system fault and flight control system fault;

[0045] The model simulation module is used for modeling and simulating any type of eVTOL aircraft core subsystem through Simulink to obtain several types of eVTOL aircraft simulation systems, the aircraft simulation system including a power supply system simulation module, a power system simulation module, a flight simulation module, a display system simulation module, an instrument system simulation module, a communication system simulation module, a sound system simulation module and a visual system simulation module;

[0046] The result generation module is used for sequentially extracting different fault data of the same fault type from the fault model library, and injecting the fault data into any aircraft simulation system to obtain unified aircraft simulation system fault instructions, sequentially bringing all fault instructions into the aircraft simulation system for fault simulation to obtain an eVTOL aircraft fault simulation design system.

[0047] The above describes one embodiment of the present application in detail, but the content is only a preferred embodiment of the present application and cannot be considered as limiting the scope of the present application. Any equivalent changes and improvements made according to the scope of the present application should still belong to the patent coverage of the present application.

Claims

1. A method for failure simulation design based on eVOTL aircraft, characterized in that, The method comprises the following steps: S1, obtaining fault data of different types of eVOTL aircraft, classifying the fault data according to a preset fault classification standard, and establishing a unified fault model library; the fault classification standard is battery system fault, electric drive system fault and flight control system fault; S2, modeling and simulating any type of eVOTL aircraft core subsystem through Simulink to obtain several types of eVOTL aircraft simulation systems, the aircraft simulation system comprising a power supply system simulation module, a power system simulation module, a flight simulation module, a display system simulation module, an instrument system simulation module, a communication system simulation module, a sound system simulation module and a visual system simulation module; S3, selecting different fault data of the same fault type from the fault model library in sequence, and injecting the fault data into any aircraft simulation system to obtain fault simulation instructions, and sequentially bringing all fault instructions into the aircraft simulation system for fault simulation to obtain an eVOTL aircraft fault simulation design system; In S3, the generation process of the fault simulation instructions is as follows: Obtain fault data corresponding to any simulation module, obtain a circuit netlist corresponding to any fault data, add fault parameters corresponding to the fault data to the circuit netlist to generate a fault circuit netlist, generate a control command file according to a preset fault duration T and the fault circuit netlist, run the control command file to obtain an actual fault duration t, if the actual fault duration t is located in the interval [T-a, T+a], then generate a fault simulation instruction according to the control command file, if the actual fault duration t is located outside the interval [T-a, T+a], then increase the fault injection times according to the current actual fault duration and generate a corresponding control command file, and generate a fault simulation instruction according to the control command file.

2. The fault simulation design method based on eVOTL aircraft according to claim 1, characterized in that, In S1, the fault data comprises battery system data, electric drive system data, flight attitude data, navigation and positioning data, communication and connection system data and sensor data.

3. The method of claim 1, wherein, In S3, the process of fault simulation is as follows: According to the fault command, control the simulation module corresponding to the fault command to run the fault circuit netlist, and interact with the remaining simulation modules in real time, so that the display system simulation module displays the crew fault warning information, the sound system simulation module broadcasts the warning sound corresponding to the fault, and the visual system simulation module displays the visual display corresponding to the fault.

4. The method of claim 3, wherein, The specific process of data interaction is as follows: Obtain preset operation data before the fault command, and the power simulation module calculates the engine thrust according to the preset operation data; the flight simulation module receives the thrust information of the engine system to calculate the aircraft state and flight state; the visual system simulation generates flight images in real time according to the aircraft state and flight state and transmits them to the display system simulation module; the display system simulation module is used for real-time display of the flight images; The power supply system simulation module calculates the power loss according to the engine thrust; The sound system simulation module provides abnormal warning information.

5. An eVOTL aircraft based failure simulation design system, characterized by, The method comprises the following steps: The data acquisition module is configured to acquire fault data of different types of eVOTL aircraft, classify the fault data according to a preset fault classification standard, and establish a unified fault model library; the fault classification standard is a battery system fault, an electric drive system fault, and a flight control system fault; The model simulation module is configured to model and simulate core subsystems of any type of eVOTL aircraft through Simulink to obtain several types of eVOTL aircraft simulation systems, the aircraft simulation system including a power supply system simulation module, a power system simulation module, a flight simulation module, a display system simulation module, an instrument system simulation module, a communication system simulation module, a sound system simulation module, and a visual system simulation module; The result generation module is configured to sequentially extract different fault data of the same fault type from the fault model library, inject the fault data into any aircraft simulation system, obtain a unified aircraft simulation system fault instruction, sequentially bring all fault instructions into the aircraft simulation system for fault simulation, and obtain an eVOTL aircraft fault simulation design system. In the result generation module, the generation process of the fault simulation instruction is as follows: acquiring fault data corresponding to any simulation module, acquiring a circuit netlist of the simulation module corresponding to any fault data, adding fault parameters corresponding to the fault data to the circuit netlist to generate a fault circuit netlist, generating a control command file according to a preset fault duration T and the fault circuit netlist, running the control command file to obtain an actual fault duration t, if the actual fault duration t is located in the interval [T-a, T+a], generating a fault simulation instruction according to the control command file, if the actual fault duration t is located outside the interval [T-a, T+a], increasing the number of fault injections according to the current actual fault duration and generating a corresponding control command file, and generating a fault simulation instruction according to the control command file.

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