Modeling Method and Device for Anti-icing and Rain Removal System of Civil Aircraft

Abstract

The present invention provides a method and device for modeling an anti-icing and rain-removing system of a civil aircraft, which relates to the technical field of simulated flight processing, and includes: determining a plurality of simulation subsystems of the anti-icing and rain-removing system of the civil aircraft based on the anti-icing and rain-removing requirements of the civil aircraft; establishing simulation models of the simulation subsystems according to the working logics of the components in the simulation subsystems; integrating the simulation models of the plurality of simulation subsystems into the anti-icing and rain-removing system of the civil aircraft according to the interaction modes and data flows among the plurality of simulation subsystems; wherein the plurality of simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem and an icing detection subsystem. The comprehensive simulation of the anti-icing and rain-removing system of the civil aircraft is realized. By adopting modular design, different subsystems can be separately functionally debugged, the simulation of the control logics of each subsystem and the simulation of fault scenarios are realized, and the prediction accuracy and reliability are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of flight simulation, and particularly to a modeling method and device for an anti-icing and rain-removing system of a civil aircraft. Background Art

[0002] Currently, the modeling methods for the anti-icing and rain-removing system of civil aircraft face several key challenges.

[0003] First of all, these modeling methods usually only focus on a single simulation object, such as wing anti-icing or nacelle anti-icing, and fail to achieve a comprehensive simulation of the entire system. This single modeling method limits the integrity of system-level function simulation, resulting in relatively less research on overall coordination and working logic simulation.

[0004] Secondly, the existing modeling methods have deficiencies in the authenticity of simulation results. Due to the lack of a comprehensive and accurate simulation of the system in a complex environment, and the lack of output of system key parameters and fault response states, these models are difficult to accurately reflect the performance of the system in actual operation. This also leads to inaccurate simulation of the output of system key parameters and fault response states, reducing the prediction accuracy and reliability of the models. Summary of the Invention

[0005] The present invention provides a modeling method and device for an anti-icing and rain-removing system of a civil aircraft, so as to solve the problems of single simulation object, incomplete function simulation, and lack of authenticity in the simulation results in the modeling method of the anti-icing and rain-removing system of a civil aircraft in the prior art.

[0006] The present invention provides a modeling method for an anti-icing and rain-removing system of a civil aircraft, including:

[0007] Based on the anti-icing and rain-removing requirements of a civil aircraft, determining several simulation subsystems of the anti-icing and rain-removing system of the civil aircraft;

[0008] According to the working logic of the components in the simulation subsystems, establishing simulation models of the simulation subsystems;

[0009] According to the interaction modes and data flows between several simulation subsystems, integrating the simulation models of several simulation subsystems into the anti-icing and rain-removing system of the civil aircraft;

[0010] Wherein, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem, and an ice detection subsystem.

[0011] A method for modeling an anti-icing and rain-removing system of a civil aircraft provided by the present invention, wherein the simulation subsystem is a wing anti-icing subsystem, and the components in the wing anti-icing subsystem include a wing anti-icing pressure switch, a wing anti-icing pressure sensor, a wing anti-icing temperature switch, and a wing anti-icing valve. According to the working logic of the components in the simulation subsystem, a simulation model of the simulation subsystem is established, including:

[0012] Respectively establish a wing anti-icing pressure switch sub-model corresponding to the wing anti-icing pressure switch, a wing anti-icing pressure sensor sub-model corresponding to the wing anti-icing pressure sensor, a wing anti-icing temperature switch sub-model corresponding to the wing anti-icing temperature switch, and a wing anti-icing valve sub-model corresponding to the wing anti-icing valve;

[0013] According to the wing anti-icing pressure switch sub-model, the wing anti-icing pressure sensor sub-model, the wing anti-icing temperature switch sub-model, the wing anti-icing temperature switch sub-model, and the wing anti-icing valve sub-model, establish a simulation model of the wing anti-icing subsystem; wherein, the wing anti-icing pressure switch sub-model is used to simulate the wing anti-icing low-pressure signal under the bleed air pressure and flow rate in the wing anti-icing pipeline in the normal working state or the fault state; the wing anti-icing pressure sensor sub-model is used to simulate the wing anti-icing pressure under the bleed air pressure and flow rate in the wing anti-icing pipeline in the normal working state or the fault state; the wing anti-icing temperature switch sub-model is used to simulate the wing anti-icing low-temperature signal under the wing anti-icing pipeline temperature in the normal working state or the fault state; the wing anti-icing valve sub-model is used to simulate the wing anti-icing valve state under the IASC wing anti-icing valve position command in the normal working state or the fault state.

[0014] A method for modeling an anti-icing and rain-removing system of a civil aircraft provided by the present invention, wherein the simulation subsystem is a nacelle anti-icing subsystem, and the components in the nacelle anti-icing subsystem include a nacelle anti-icing valve and a nacelle anti-icing pressure sensor. According to the working logic of the components in the simulation subsystem, a simulation model of the simulation subsystem is established, including:

[0015] Respectively establish a nacelle anti-icing valve sub-model corresponding to the nacelle anti-icing valve and a nacelle anti-icing pressure sensor sub-model corresponding to the nacelle anti-icing pressure sensor;

[0016] According to the nacelle anti-icing valve sub-model and the nacelle anti-icing pressure sensor sub-model, establish a simulation model of the nacelle anti-icing subsystem;

[0017] Wherein, the nacelle anti-icing valve sub-model is used to simulate the nacelle anti-icing valve state under the 5-level pressure output by the press and the nacelle anti-icing control panel signal in the normal working state or the fault state; the nacelle anti-icing pressure sensor sub-model is used to simulate the nacelle anti-icing pressure under the nacelle anti-icing bleed air pressure in the normal working state or the fault state.

[0018] A modeling method for an anti-icing and rain-removing system of a civil aircraft provided by the present invention, wherein the simulation subsystem is a windshield heating subsystem, and the components in the windshield heating subsystem include a windshield heating controller and a windshield heater. According to the working logic of the components in the simulation subsystem, establishing a simulation model of the simulation subsystem includes:

[0019] Respectively establishing a windshield heating controller sub-model corresponding to the windshield heating controller and a windshield heater sub-model corresponding to the windshield heater;

[0020] According to the windshield heating controller sub-model and the windshield heater sub-model, establishing a simulation model of the windshield heating subsystem;

[0021] Wherein, the windshield heating controller sub-model is used to simulate the windshield working state and the ventilation window working state under the first power supply signal and the windshield heating control panel signal in a normal working state or a fault state; the windshield heater sub-model is used to simulate the windshield heating parameters and the ventilation window heating parameters under the first simulation result output by the windshield heating controller sub-model in a normal working state or a fault state.

[0022] A modeling method for an anti-icing and rain-removing system of a civil aircraft provided by the present invention, wherein the simulation subsystem is a probe heating subsystem, and the components in the probe heating subsystem include a probe heating controller and a probe heater. According to the working logic of the components in the simulation subsystem, establishing a simulation model of the simulation subsystem includes:

[0023] Respectively establishing a probe heating controller sub-model corresponding to the probe heating controller and a probe heater sub-model corresponding to the probe heater;

[0024] According to the probe heating controller sub-model and the probe heater sub-model, establishing a simulation model of the probe heating subsystem;

[0025] Wherein, the probe heating controller sub-model is used to simulate the total static pressure, the standby total static pressure probe heating state and the total temperature sensor heating signal under the second power supply signal and the probe heating control panel signal in a normal working state or a fault state; the probe heater sub-model is used to simulate the probe heating power under the aircraft airspeed and the second simulation result output by the probe heating controller sub-model in a normal working state or a fault state.

[0026] A modeling method for an anti-icing and rain-removing system of a civil aircraft provided by the present invention, wherein the simulation subsystem is a windshield wiper subsystem, and the components in the windshield wiper subsystem include a windshield wiper controller. According to the working logic of the components in the simulation subsystem, establishing a simulation model of the simulation subsystem includes:

[0027] Establish a windshield wiper controller sub-model corresponding to the windshield wiper controller;

[0028] According to the windshield wiper controller sub-model, establish a simulation model of the windshield wiper subsystem;

[0029] Among them, the windshield wiper controller sub-model is used to simulate the working state of the windshield wiper under the manual control signal of the windshield rain removal control panel in the normal working state or the fault state.

[0030] According to a modeling method for the anti-icing and rain-removing system of a civil aircraft provided by the present invention, the simulation subsystem is an ice detection subsystem, and the components in the ice detection subsystem include an ice detector. According to the working logic of the components in the simulation subsystem, establish a simulation model of the simulation subsystem, including:

[0031] Establish an ice detector sub-model corresponding to the ice detector;

[0032] According to the ice detector sub-model, establish a simulation model of the ice detection subsystem;

[0033] Among them, the ice detector sub-model is used to simulate the self-test state, ice signal, working mode and working state of the ice detector under the third power supply signal, ice detection self-test signal and ice environment parameters in the normal working state or the fault state.

[0034] The present invention also provides a modeling device for the anti-icing and rain-removing system of a civil aircraft, including:

[0035] The first modeling module is used to determine several simulation subsystems of the anti-icing and rain-removing system of the civil aircraft based on the anti-icing and rain-removing requirements of the civil aircraft;

[0036] The second modeling module is used to establish a simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem;

[0037] The third modeling module is used to integrate the simulation models of several simulation subsystems into the anti-icing and rain-removing system of the civil aircraft according to the interaction mode and data flow between several simulation subsystems;

[0038] Among them, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem and an ice detection subsystem.

[0039] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, the method for modeling the anti-icing and rain-removing system of a civil aircraft as described in any one of the above is implemented.

[0040] The present invention also provides a non-transitory computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the method for modeling the anti-icing and rain-removing system of an aircraft as described in any one of the above is implemented.

[0041] The present invention also provides a computer program product, including a computer program. When the computer program is executed by a processor, the method for modeling the anti-icing and rain-removing system of a civil aircraft as described in any one of the above is implemented.

[0042] The method and device for modeling the anti-icing and rain-removing system of a civil aircraft provided by the present invention determine several simulation subsystems of the anti-icing and rain-removing system of a civil aircraft based on the anti-icing and rain-removing requirements of the civil aircraft; establish simulation models of the simulation subsystems according to the working logics of the components in the simulation subsystems; integrate the simulation models of the several simulation subsystems into the anti-icing and rain-removing system of the civil aircraft according to the interaction modes and data flows between the several simulation subsystems; wherein, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem, and an icing detection subsystem. The solution of the embodiment of the present application can realize the comprehensive simulation of the entire system. By adopting a modular design, different subsystems can be debugged separately in terms of functions, so as to realize the simulation of the control logics of each subsystem and the simulation of fault scenarios, improving the prediction accuracy and reliability. Description of the Drawings

[0043] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0044] Figure 1 It is a schematic flowchart of the method for modeling the anti-icing and rain-removing system of a civil aircraft provided by the embodiment of the present application;

[0045] Figure 2 It is a schematic diagram of the application scenario of the simulation model of the wing anti-icing subsystem provided by the embodiment of the present application;

[0046] Figure 3 It is a schematic diagram of the application scenario of the simulation model of the nacelle anti-icing subsystem provided by the embodiment of the present application;

[0047] Figure 4Schematic diagram of the application scenario of the simulation model of the windshield heating subsystem provided by the embodiment of the present application;

[0048] Figure 5 Schematic diagram of the application scenario of the simulation model of the probe heating subsystem provided by the embodiment of the present application;

[0049] Figure 6 Schematic diagram of the application scenario of the simulation model of the windshield wiper subsystem provided by the embodiment of the present application;

[0050] Figure 7 Schematic diagram of the application scenario of the simulation model of the ice detection subsystem provided by the embodiment of the present application;

[0051] Figure 8 Schematic diagram of the structure of the civil aircraft anti-icing and rain-removing system modeling device provided by the embodiment of the present application;

[0052] Figure 9 Schematic diagram of the structure of the electronic device provided by the present invention. Detailed implementation manners

[0053] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below with reference to the accompanying drawings in the present invention. Apparently, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art without creative efforts based on the embodiments in the present invention belong to the scope of protection of the present invention.

[0054] Figure 1 Schematic diagram of the process of the civil aircraft anti-icing and rain-removing system modeling method provided by the embodiment of the present application, as Figure 1 shown, including: step 110, step 120 and step 130.

[0055] Step 110: Based on the anti-icing and rain-removing requirements of civil aircraft, determine several simulation subsystems of the civil aircraft anti-icing and rain-removing system.

[0056] Among them, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem and an ice detection subsystem.

[0057] In this embodiment, the key functional parts that need to be simulated in the civil aircraft anti-icing and rain-removing system are identified and analyzed, and they are defined as independent simulation subsystems. Each simulation subsystem represents one or more functional areas in a real aircraft, such as wing anti-icing, nacelle anti-icing, windshield heating, etc.

[0058] Step 120: Establish a simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem.

[0059] In this embodiment, information such as the working logic, parameters, and state changes of the components involved in each simulation subsystem during actual operation is determined. Based on the collected relevant information, the structure and algorithm of the simulation model of each simulation subsystem are designed.

[0060] Step 130: Integrate the simulation models of several simulation subsystems into the civil aircraft anti-icing and rain removal system according to the interaction mode and data flow between the several simulation subsystems.

[0061] In this step, during the integration process, first define the interfaces and data formats for each simulation subsystem to interact with other simulation subsystems, and then write the corresponding logic code to connect each simulation subsystem and ensure that the data flow between them can be correctly transmitted.

[0062] In the embodiment of the present application, based on the anti-icing and rain removal requirements of civil aircraft, several simulation subsystems of the civil aircraft anti-icing and rain removal system are determined; according to the working logic of the components in the simulation subsystem, a simulation model of the simulation subsystem is established; according to the interaction mode and data flow between several simulation subsystems, the simulation models of several simulation subsystems are integrated into the civil aircraft anti-icing and rain removal system; wherein, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem, and an icing detection subsystem. The solution of the embodiment of the present application can achieve a comprehensive simulation of the entire system. By adopting a modular design, different subsystems can be individually functionally debugged to realize the simulation of the control logic of each subsystem and the simulation of fault scenarios, improving the prediction accuracy and reliability.

[0063] In some embodiments, with reference to Figure 2 , the simulation subsystem is a wing anti-icing subsystem, and the components in the wing anti-icing subsystem include a wing anti-icing pressure switch, a wing anti-icing pressure sensor, a wing anti-icing temperature switch, and a wing anti-icing valve. Establishing the simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem includes:

[0064] Respectively establish a wing anti-icing pressure switch sub-model corresponding to the wing anti-icing pressure switch, a wing anti-icing pressure sensor sub-model corresponding to the wing anti-icing pressure sensor, a wing anti-icing temperature switch sub-model corresponding to the wing anti-icing temperature switch, and a wing anti-icing valve sub-model corresponding to the wing anti-icing valve;

[0065] Based on the wing anti-ice pressure switch sub-model, wing anti-ice pressure sensor sub-model, wing anti-ice temperature switch sub-model, wing anti-ice temperature switch sub-model, and wing anti-ice valve sub-model, establish a simulation model of the wing anti-ice subsystem; wherein, the wing anti-ice pressure switch sub-model is used to simulate the wing anti-ice low-pressure signal under the bleed air pressure and flow rate in the wing anti-ice pipeline in normal working conditions or fault conditions; the wing anti-ice pressure sensor sub-model is used to simulate the wing anti-ice pressure under the bleed air pressure and flow rate in the wing anti-ice pipeline in normal working conditions or fault conditions; the wing anti-ice temperature switch sub-model is used to simulate the wing anti-ice low-temperature signal under the wing anti-ice pipeline temperature in normal working conditions or fault conditions; the wing anti-ice valve sub-model is used to simulate the wing anti-ice valve state under the IASC wing anti-ice valve position command in normal working conditions or fault conditions.

[0066] In this embodiment, the wing anti-ice subsystem is used to ensure that the wings of the aircraft do not ice up under cold or icing conditions, thus affecting flight safety. The wing anti-ice subsystem includes multiple key components, such as a wing anti-ice pressure switch, a wing anti-ice pressure sensor, a wing anti-ice temperature switch, and a wing anti-ice valve.

[0067] In the wing anti-ice pressure switch sub-model, the activation threshold of the pressure switch is preset in advance to simulate the response of the wing anti-ice pressure switch when the pressure change in the wing anti-ice pipeline reaches or exceeds the set activation threshold, that is, to issue a wing anti-ice low-pressure signal. In addition, in this embodiment, the influence of the flow rate change on the pressure is indirectly measured. For example, an increase in the flow rate may cause the pressure in the pipeline to rise, thus triggering the activation of the pressure switch.

[0068] In addition, in addition to simulating the response in the normal state, the response in the fault state is also simulated. For example, the switch gets stuck (unable to open or close). For the fault signal of the stuck switch, the wing anti-ice pressure switch sub-model will simulate that the wing anti-ice pressure switch remains in a certain state (open or closed) regardless of the pressure and flow rate changes in the wing anti-ice pipeline.

[0069] In the wing anti-ice pressure sensor sub-model, the output values of the pressure sensor under different wing anti-ice pipeline pressures and flow rates are preset in advance to simulate the wing anti-ice pressure output by the wing anti-ice pressure sensor under different pressures and flow rates in the wing anti-ice pipeline. In addition, in addition to simulating the output results in the normal state, the output results in the fault state are also simulated. For example, the sensor fails, no output or a fixed output value.

[0070] In the wing anti-ice temperature switch sub-model, the activation threshold of the temperature switch is preset in advance to simulate the response of the wing anti-ice temperature switch when the temperature change in the wing anti-ice pipeline reaches or exceeds the set activation threshold, that is, to issue a wing anti-ice low-temperature signal.

[0071] In addition to simulating the response in the normal state, it will also simulate the response in the fault state, such as the switch getting stuck (unable to open or close). For the fault signal of the switch getting stuck, the wing anti-ice temperature switch sub-model will simulate that the wing anti-ice temperature switch remains in a certain state (open or closed) regardless of the temperature change in the wing anti-ice pipeline.

[0072] The wing anti-ice valve sub-model will first simulate receiving the wing anti-ice valve position instructions from the IASC system. These instructions are usually electronic signals indicating to which position the wing anti-ice valve (left wing anti-ice valve or right wing anti-ice valve) should be opened. According to the received instructions, the wing anti-ice valve model will simulate the wing anti-ice valve to make corresponding position adjustments. For example, if the instruction requires the left wing anti-ice valve to be fully opened, the model will simulate the left wing anti-ice valve gradually opening from the closed state to the maximum position.

[0073] In addition to simulating the response in the normal state, it will also simulate the response in the fault state, such as the valve getting stuck (unable to move or having restricted movement). For the case of the valve getting stuck, the model will simulate that the valve cannot respond to the IASC instruction and remains in the current position or cannot move to the specified position.

[0074] In this embodiment, based on the sub-models of the above four components, a simulation model of the overall wing anti-ice subsystem can be established. This simulation model can simulate the behavior of the entire subsystem in the normal working state and the fault state, thus providing a virtual environment for testers to analyze and test.

[0075] In some embodiments, referring to Figure 3 , the simulation subsystem is the nacelle anti-ice subsystem. The components in the nacelle anti-ice subsystem include the nacelle anti-ice valve and the nacelle anti-ice pressure sensor. Establishing the simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem includes:

[0076] Respectively establish the nacelle anti-ice valve sub-model corresponding to the nacelle anti-ice valve and the nacelle anti-ice pressure sensor sub-model corresponding to the nacelle anti-ice pressure sensor;

[0077] According to the nacelle anti-ice valve sub-model and the nacelle anti-ice pressure sensor sub-model, establish the simulation model of the nacelle anti-ice subsystem;

[0078] Among them, the nacelle anti-ice valve sub-model is used to simulate the nacelle anti-ice valve state under the 5-level pressure output by the press and the nacelle anti-ice control panel signal in the normal working state or the fault state; the nacelle anti-ice pressure sensor sub-model is used to simulate the nacelle anti-ice pressure under the nacelle anti-ice bleed air pressure in the normal working state or the fault state.

[0079] The nacelle anti-ice valve sub-model simulates the behavior of the nacelle anti-ice valve in the normal state (such as the left nacelle anti-ice valve or the right nacelle anti-ice valve) when receiving the 5th level pressure output from the press and the nacelle anti-ice control panel signal. The nacelle anti-ice valve adjusts its opening according to these signals to control the air flow rate into the nacelle anti-ice system.

[0080] In addition to simulating the response in the normal state, the response in the fault state will also be simulated, such as the valve being unable to respond to the control signal, unable to fully open or close, or staying at a non-instructed position, etc.

[0081] The nacelle anti-ice pressure sensor sub-model simulates the behavior of the nacelle anti-ice pressure sensor. The output values of the nacelle anti-ice pressure sensor at different nacelle anti-ice bleed air pressures are preset in the nacelle anti-ice pressure sensor sub-model. In addition to simulating the output results in the normal state, the output results in the fault state will also be simulated, such as sensor failure, no output or fixed output value.

[0082] In this embodiment, according to the sub-models of the above two components, a simulation model of the overall nacelle anti-ice subsystem can be established. This simulation model can simulate the behavior of the entire subsystem in the normal working state and the fault state.

[0083] In some embodiments, referring to Figure 4 , the simulation subsystem is a windshield heating subsystem, and the components in the windshield heating subsystem include a windshield heating controller and a windshield heater. According to the working logic of the components in the simulation subsystem, establishing the simulation model of the simulation subsystem includes:

[0084] Respectively establish a windshield heating controller sub-model corresponding to the windshield heating controller and a windshield heater sub-model corresponding to the windshield heater;

[0085] According to the windshield heating controller sub-model and the windshield heater sub-model, establish the simulation model of the windshield heating subsystem;

[0086] Among them, the windshield heating controller sub-model is used to simulate the windshield working state and the ventilation window working state under the first power supply signal and the windshield heating control panel signal in the normal working state or the fault state; the windshield heater sub-model is used to simulate the windshield heating parameters and the ventilation window heating parameters under the first simulation result output by the windshield heating controller sub-model in the normal working state or the fault state.

[0087] The windshield heating controller sub-model is used to simulate the behavior of the windshield heating controller when receiving the first power supply signal (i.e., AC power supply signal) and the windshield heating control panel signal in normal working conditions or fault conditions. That is, the windshield heating controller controls the working states of the windshield and the ventilation window according to these signals. For example, the transparency of the windshield and the ventilation window in normal conditions. Output an incorrect control signal in fault conditions.

[0088] The windshield heater sub-model simulates the behavior of the windshield heater when receiving the control signal from the windshield heating controller. The windshield heater adjusts the heating parameters according to these signals. For example, in normal working conditions, the windshield heater accurately adjusts the heating parameters according to the instructions of the controller, such as heating power, heating time, etc. Simulate that in fault conditions, the windshield heater cannot respond to the control signal or outputs incorrect heating parameters.

[0089] In this embodiment, according to the sub-models of the above two components, a simulation model of the overall windshield heating subsystem can be established. This simulation model can simulate the behavior of the entire subsystem in normal working conditions and fault conditions.

[0090] In some embodiments, referring to Figure 5 , the simulation subsystem is a probe heating subsystem. The components in the probe heating subsystem include a probe heating controller and a probe heater. Establishing the simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem includes:

[0091] Respectively establish a probe heating controller sub-model corresponding to the probe heating controller and a probe heater sub-model corresponding to the probe heater;

[0092] Establish the simulation model of the probe heating subsystem according to the probe heating controller sub-model and the probe heater sub-model;

[0093] Among them, the probe heating controller sub-model is used to simulate the total pressure, standby total pressure probe heating state and total temperature sensor heating signal under the second power supply signal and the probe heating control panel signal in normal working conditions or fault conditions; the probe heater sub-model is used to simulate the probe heating power under the aircraft airspeed in normal working conditions or fault conditions and the second simulation result output by the probe heating controller sub-model.

[0094] The probe heating controller sub-model is used to simulate the behavior of the probe heating controller when receiving the second power supply signal (such as a DC power supply signal or an AC power supply signal) and the probe heating control panel signal. The probe heating controller controls the heating states of the total pressure and static pressure probe, the standby total pressure and static pressure probe, and the total temperature sensor based on these signals. The simulation content includes the response signals in normal operating conditions and fault conditions. For example, the controller cannot start, cannot turn off the heating, or outputs an incorrect heating power due to an incorrect control signal being output.

[0095] The probe heater sub-model is used to simulate the probe heating power output by the probe heater when receiving the aircraft airspeed parameter and the control signal from the probe heating controller. The simulation content includes the probe heating power output in normal operating conditions and the inability to respond to the control signal or the output of an incorrect probe heating power in fault conditions.

[0096] In this embodiment, based on the sub-models of the above two components, a simulation model of the overall probe heating subsystem can be established. This simulation model can simulate the behavior of the entire subsystem in normal operating conditions and fault conditions.

[0097] In some embodiments, referring to Figure 6 , the simulation subsystem is a windshield wiper subsystem, and the components in the windshield wiper subsystem include a windshield wiper controller. Establishing the simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem includes:

[0098] Establishing a windshield wiper controller sub-model corresponding to the windshield wiper controller;

[0099] Based on the windshield wiper controller sub-model, establishing the simulation model of the windshield wiper subsystem;

[0100] Among them, the windshield wiper controller sub-model is used to simulate the working state of the windshield wiper under the manual control signal of the windshield rain removal control panel in normal operating conditions or fault conditions.

[0101] The windshield wiper controller sub-model is used to simulate the response of the windshield wiper controller after receiving the manual control signal (such as the left windshield wiper control signal) issued by the windshield rain removal control panel. These signals include instructions such as start, stop, and change the wiper speed.

[0102] The simulation content is divided into how the windshield wiper controller accurately controls the windshield wiper according to the received signals in normal operating conditions. For example, when receiving a stop signal, the wiper stops; when receiving a signal to change the speed, the wiper adjusts its working speed. In fault conditions, the abnormal behaviors of the windshield wiper controller. For example, it cannot respond to the control signal, outputs an incorrect control signal (such as the wiper continues to work after receiving a stop signal), etc.

[0103] In this embodiment, according to the sub-models of the above windshield wiper controller assembly, a simulation model of the overall windshield wiper subsystem can be established. This simulation model can simulate the behavior of the entire subsystem in normal operating conditions and fault conditions.

[0104] In some embodiments, referring to Figure 7 , the simulation subsystem is an icing detection subsystem, and the components in the icing detection subsystem include an icing detector. Establishing the simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem includes:

[0105] Establishing an icing detector sub-model corresponding to the icing detector;

[0106] Establishing the simulation model of the icing detection subsystem according to the icing detector sub-model;

[0107] Wherein, the icing detector sub-model is used to simulate the self-test state, icing signal, working mode and working state of the icing detector under the third power supply signal, icing detection self-test signal and icing environment parameters in normal operating conditions or fault conditions.

[0108] The icing detector sub-model is used to simulate the behavior of the icing detector when receiving the third power supply signal (such as a DC power supply signal), the icing detection self-test signal, and different icing environment parameters (such as temperature, humidity, pressure, etc.), that is, the self-test state of the icing detector, the output of the icing signal, the working mode and the working state.

[0109] The simulation content is divided into the self-test state information output after self-test when the icing detector receives the self-test signal under normal operating conditions. When the icing environment parameters reach the preset threshold, the icing signal output by the icing detector, the decision-making working mode and the working state, etc. In addition, it will also simulate that in the fault condition, the icing detector fails to output an incorrect icing signal or cannot work, etc.

[0110] In this embodiment, according to the sub-models of the above icing detector assembly, a simulation model of the overall icing detection subsystem can be established. This simulation model can simulate the behavior of the entire subsystem in normal operating conditions and fault conditions.

[0111] The civil aircraft anti-icing and rain-removing system modeling device provided by the present invention will be described below. The civil aircraft anti-icing and rain-removing system modeling device described below can be mutually referred to the civil aircraft anti-icing and rain-removing system modeling method described above.

[0112] Figure 8Schematic structural diagram of a civil aircraft anti-icing and rain-removing system modeling device provided by an embodiment of the present application, as shown in Figure 8 shown, including: a first modeling module 810, a second modeling module 820, and a third modeling module 830.

[0113] The first modeling module 810 is configured to determine several simulation subsystems of the civil aircraft anti-icing and rain-removing system based on the anti-icing and rain-removing requirements of the civil aircraft.

[0114] The second modeling module 820 is configured to establish a simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem.

[0115] The third modeling module 830 is configured to integrate the simulation models of several simulation subsystems into the civil aircraft anti-icing and rain-removing system according to the interaction mode and data flow between several simulation subsystems.

[0116] Among them, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem, and an ice detection subsystem.

[0117] In the embodiment of the present application, a comprehensive simulation of the entire system is realized. By adopting a modular design, different subsystems can be individually functionally debugged to realize the simulation of the control logic of each subsystem and the simulation of fault scenarios, improving the prediction accuracy and reliability.

[0118] Figure 9 Schematic structural diagram of an electronic device provided by the present invention, as shown in Figure 9 shown, the electronic device may include: a processor 910, a communication interface 920, a memory 930, and a communication bus 940. Among them, the processor 910, the communication interface 920, and the memory 930 complete communication with each other through the communication bus 940. The processor 910 can call the logic instructions in the memory 930 to execute the civil aircraft anti-icing and rain-removing system modeling method, and the method includes: determining several simulation subsystems of the aircraft anti-icing and rain-removing system based on the anti-icing and rain-removing requirements of the civil aircraft; establishing a simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem; integrating the simulation models of several simulation subsystems into the civil aircraft anti-icing and rain-removing system according to the interaction mode and data flow between several simulation subsystems; among them, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem, and an ice detection subsystem.

[0119] In addition, when the logical instructions in the above-mentioned memory 930 are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or a part of this technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present invention. The aforementioned storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memories (ROMs), random access memories (RAMs), magnetic disks, or optical discs that can store program codes.

[0120] On the other hand, the present invention also provides a computer program product. The computer program product includes a computer program that can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the civil aircraft anti-icing and rain removal system modeling method provided by the above-mentioned various methods. The method includes: based on the civil aircraft anti-icing and rain removal requirements, determining several simulation subsystems of the civil aircraft anti-icing and rain removal system; establishing simulation models of the simulation subsystems according to the working logics of the components in the simulation subsystems; integrating the simulation models of the several simulation subsystems into the civil aircraft anti-icing and rain removal system according to the interaction modes and data flows between the several simulation subsystems; wherein, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem, and an icing detection subsystem.

[0121] On another aspect, the present invention also provides a non-transitory computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it realizes the civil aircraft anti-icing and rain removal system modeling method provided by the above-mentioned various methods. The method includes: based on the civil aircraft anti-icing and rain removal requirements, determining several simulation subsystems of the civil aircraft anti-icing and rain removal system; establishing simulation models of the simulation subsystems according to the working logics of the components in the simulation subsystems; integrating the simulation models of the several simulation subsystems into the civil aircraft anti-icing and rain removal system according to the interaction modes and data flows between the several simulation subsystems; wherein, the several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem, and an icing detection subsystem.

[0122] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art can understand and implement it without creative efforts.

[0123] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the essence of the above technical solution, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions for causing a computer device (which can be a personal computer, server, or network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0124] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments or equivalently replace some of the technical features. These modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A modeling method for a civil aircraft anti-icing and rain removal system, characterized in that: include: Based on the requirements of civil aircraft anti-icing and rain removal, several simulation subsystems of civil aircraft anti-icing and rain removal systems are determined; Establishing a simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem; Integrating simulation models of several simulation subsystems into the civil aircraft anti-icing and rain removal system according to the interaction mode and data flow between the several simulation subsystems; The several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem and an ice detection subsystem; The simulation subsystem is a wing anti-icing subsystem, and the components in the wing anti-icing subsystem include a wing anti-icing pressure switch, a wing anti-icing pressure sensor, a wing anti-icing temperature switch, and a wing anti-icing valve, and further include: Establishing a wing anti-icing pressure switch sub-model corresponding to the wing anti-icing pressure switch, a wing anti-icing pressure sensor sub-model corresponding to the wing anti-icing pressure sensor, a wing anti-icing temperature switch sub-model corresponding to the wing anti-icing temperature switch, and a wing anti-icing valve sub-model corresponding to the wing anti-icing valve respectively; Establishing a simulation model of the wing anti-icing subsystem according to the wing anti-icing pressure switch sub-model, the wing anti-icing pressure sensor sub-model, the wing anti-icing temperature switch sub-model, and the wing anti-icing valve sub-model; Among them, the wing anti-icing pressure switch sub-model is used to simulate the wing anti-icing low pressure signal under the bleed air pressure and flow in the wing anti-icing pipeline in normal working state or fault state; the wing anti-icing pressure sensor sub-model is used to simulate the wing anti-icing pressure under the bleed air pressure and flow in the wing anti-icing pipeline in normal working state or fault state; the wing anti-icing temperature switch sub-model is used to simulate the wing anti-icing low temperature signal under the wing anti-icing pipeline temperature in normal working state or fault state; the wing anti-icing valve sub-model is used to simulate the wing anti-icing valve state under the wing anti-icing valve position instruction issued by the IASC system in normal working state or fault state.

2. The modeling method of the civil aircraft anti-icing and rain removal system according to claim 1 is characterized in that: The simulation subsystem is a nacelle anti-icing subsystem, and the components in the nacelle anti-icing subsystem include a nacelle anti-icing valve and a nacelle anti-icing pressure sensor. The simulation model of the simulation subsystem is established according to the working logic of the components in the simulation subsystem, including: Establishing a nacelle anti-icing valve sub-model corresponding to the nacelle anti-icing valve and a nacelle anti-icing pressure sensor sub-model corresponding to the nacelle anti-icing pressure sensor respectively; Establishing a simulation model of the nacelle anti-icing subsystem according to the nacelle anti-icing valve sub-model and the nacelle anti-icing pressure sensor sub-model; Among them, the nacelle anti-icing valve sub-model is used to simulate the 5-level pressure output by the press and the nacelle anti-icing valve status under the nacelle anti-icing control panel signal in normal working state or fault state; the nacelle anti-icing pressure sensor sub-model is used to simulate the nacelle anti-icing pressure under the nacelle anti-icing bleed air pressure in normal working state or fault state.

3. The modeling method of the civil aircraft anti-icing and rain removal system according to claim 1 is characterized in that: The simulation subsystem is a windshield heating subsystem, and the components in the windshield heating subsystem include a windshield heating controller and a windshield heater. The simulation model of the simulation subsystem is established according to the working logic of the components in the simulation subsystem, including: Respectively establishing a windshield heating controller sub-model corresponding to the windshield heating controller and a windshield heater sub-model corresponding to the windshield heater; Establishing a simulation model of the windshield heating subsystem according to the windshield heating controller submodel and the windshield heater submodel; Among them, the windshield heating controller sub-model is used to simulate the windshield working state and the ventilation window working state under the first power supply signal and the windshield heating control panel signal in normal working state or fault state; the windshield heater sub-model is used to simulate the windshield heating parameters and the ventilation window heating parameters under the first simulation result output by the windshield heating controller sub-model in normal working state or fault state.

4. The modeling method of the civil aircraft anti-icing and rain removal system according to claim 1, characterized in that: The simulation subsystem is a probe heating subsystem, and the components in the probe heating subsystem include a probe heating controller and a probe heater. According to the working logic of the components in the simulation subsystem, a simulation model of the simulation subsystem is established, including: Respectively establishing a probe heating controller sub-model corresponding to the probe heating controller and a probe heater sub-model corresponding to the probe heater; Establishing a simulation model of the probe heating subsystem according to the probe heating controller submodel and the probe heater submodel; Among them, the probe heating controller sub-model is used to simulate the full static pressure, standby full static pressure probe heating state and the total temperature sensor heating signal under the second power supply signal and the probe heating control panel signal in normal working state or fault state; the probe heater sub-model is used to simulate the aircraft airspeed in normal working state or fault state and the probe heating power under the second simulation result output by the probe heating controller sub-model.

5. The modeling method for anti-icing and rain removal system of a civil aircraft according to claim 1, characterized in that: The simulation subsystem is a windshield wiper subsystem, and the components in the windshield wiper subsystem include a windshield wiper controller. The simulation model of the simulation subsystem is established according to the working logic of the components in the simulation subsystem, including: Establishing a windshield wiper controller sub-model corresponding to the windshield wiper controller; According to the windshield wiper controller sub-model, establishing a simulation model of the windshield wiper sub-system; The windshield wiper controller sub-model is used to simulate the working state of the windshield wiper under the manual control signal of the windshield rain removal control panel in normal working state or fault state.

6. The modeling method of the civil aircraft anti-icing and rain removal system according to claim 1, characterized in that: The simulation subsystem is an ice detection subsystem, and the components in the ice detection subsystem include ice detectors. The simulation model of the simulation subsystem is established according to the working logic of the components in the simulation subsystem, including: Establishing an ice detector sub-model corresponding to the ice detector; According to the ice detector sub-model, a simulation model of the ice detection subsystem is established; Among them, the ice detector sub-model is used to simulate the third power supply signal, ice detection self-test signal and ice detector self-test state, ice signal, ice detector working mode and ice detector working state under ice environment parameters in normal working state or fault state.

7. A modeling device for a civil aircraft anti-icing and rain removal system, characterized in that: include: The first modeling module is used to determine several simulation subsystems of the civil aircraft anti-icing and rain removal system based on the anti-icing and rain removal requirements of the civil aircraft; A second modeling module, used to establish a simulation model of the simulation subsystem according to the working logic of the components in the simulation subsystem; A third modeling module is used to integrate simulation models of several simulation subsystems into the civil aircraft anti-icing and rain removal system according to the interaction mode and data flow between the several simulation subsystems; The several simulation subsystems include a wing anti-icing subsystem, a nacelle anti-icing subsystem, a windshield heating subsystem, a probe heating subsystem, a windshield wiper subsystem and an ice detection subsystem; The simulation subsystem is a wing anti-icing subsystem, and the components in the wing anti-icing subsystem include a wing anti-icing pressure switch, a wing anti-icing pressure sensor, a wing anti-icing temperature switch, and a wing anti-icing valve, and further include: Establishing a wing anti-icing pressure switch sub-model corresponding to the wing anti-icing pressure switch, a wing anti-icing pressure sensor sub-model corresponding to the wing anti-icing pressure sensor, a wing anti-icing temperature switch sub-model corresponding to the wing anti-icing temperature switch, and a wing anti-icing valve sub-model corresponding to the wing anti-icing valve respectively; Establishing a simulation model of the wing anti-icing subsystem according to the wing anti-icing pressure switch sub-model, the wing anti-icing pressure sensor sub-model, the wing anti-icing temperature switch sub-model, and the wing anti-icing valve sub-model; Among them, the wing anti-icing pressure switch sub-model is used to simulate the wing anti-icing low pressure signal under the bleed air pressure and flow in the wing anti-icing pipeline in normal working state or fault state; the wing anti-icing pressure sensor sub-model is used to simulate the wing anti-icing pressure under the bleed air pressure and flow in the wing anti-icing pipeline in normal working state or fault state; the wing anti-icing temperature switch sub-model is used to simulate the wing anti-icing low temperature signal under the wing anti-icing pipeline temperature in normal working state or fault state; the wing anti-icing valve sub-model is used to simulate the wing anti-icing valve state under the wing anti-icing valve position instruction issued by the IASC system in normal working state or fault state.

8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the modeling method of the anti-icing and rain removal system of a civil aircraft as claimed in any one of claims 1 to 6 is implemented.

9. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the modeling method of the anti-icing and rain removal system of a civil aircraft as claimed in any one of claims 1 to 6 is implemented.

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