Intelligent deicing method and system based on ultrasonic detection, medium and equipment

Abstract

The invention discloses an intelligent deicing method and system based on ultrasonic detection, a medium and equipment, and relates to the technical field of deicing. The intelligent deicing method based on ultrasonic detection is used for the intelligent deicing system and comprises the following steps that the surface temperature of an airplane is detected based on an infrared sensor, and the surface temperature value of the airplane is obtained; comparing the airplane surface temperature value with a temperature threshold value; if the aircraft surface temperature value is greater than the temperature threshold value, continuing to detect the aircraft surface temperature based on the infrared sensor; if the aircraft surface temperature value is smaller than or equal to the temperature threshold value, an ultrasonic pulse echo icing sensor is started to detect the icing thickness of the aircraft surface, and icing signal information is obtained; and based on the icing signal information, whether the automatic deicing system of the airplane is started for deicing treatment is judged. Through the steps, the deicing efficiency of the aircraft during flight is improved.

Description

Technical Field

[0001] The present application relates to the technical field of deicing, and in particular to an intelligent deicing method, system, medium and equipment based on ultrasonic detection. Background Art

[0002] During flight, icing is a serious aviation safety issue, as it may cause flight control system failure or even cause an accident. There have been many flight accidents related to icing around the world, which makes the importance of aircraft ice detection devices more and more significant. These devices can detect ice on the aircraft surface in a timely manner, provide key information to pilots, and help them take necessary de-icing measures, thereby reducing the risks caused by icing.

[0003] However, the icing sensors installed on most aircraft can only perform qualitative identification, that is, they can only determine whether icing has occurred, but cannot accurately quantify the severity of icing. This limitation leads to low efficiency of de-icing systems and makes it difficult for pilots to accurately assess the risk status of the aircraft when facing icing. Summary of the invention

[0004] The present application provides an intelligent deicing method, system, medium and equipment based on ultrasonic detection, which at least solves the technical problem of low efficiency in deicing in the prior art.

[0005] In order to solve the above technical problems, the present application provides an intelligent deicing method based on ultrasonic detection, which is used in an intelligent deicing system. The method comprises the following steps: Detecting the aircraft surface temperature based on an infrared sensor to obtain an aircraft surface temperature value; comparing the aircraft surface temperature value with a temperature threshold; If the aircraft surface temperature value is greater than the temperature threshold, continue to detect the aircraft surface temperature based on the infrared sensor; If the aircraft surface temperature value is less than or equal to the temperature threshold, the ultrasonic pulse echo icing sensor is turned on to detect the ice thickness on the aircraft surface to obtain icing signal information; Based on the icing signal information, it is determined whether to start the automatic de-icing system of the aircraft to perform de-icing processing.

[0006] As some optional implementations of the present application, if the aircraft surface temperature value is less than or equal to the temperature threshold, the step of starting the ultrasonic pulse echo icing sensor to detect the ice thickness on the aircraft surface and obtaining icing signal information includes: If the aircraft surface temperature value is less than or equal to the temperature threshold, the target area is photographed based on the image acquisition device to obtain multiple images of the target area; the target area refers to an area where the surface temperature value is less than or equal to the temperature threshold; Inputting the images of each target area into the trained target recognition model to obtain target area information corresponding to the images of each target area; the target area information includes the target area location and the icing difficulty level value of the target area; Based on the target area information, the ultrasonic pulse echo icing sensor is turned on to detect the ice thickness of the target area to obtain the ice layer thickness of the target area.

[0007] As some optional implementations of the present application, the target recognition model is trained by the following steps: Acquire an aircraft image set; the aircraft image set includes aircraft images of different models of aircraft at different angles and in different states; Performing feature annotation on each region in the aircraft image to obtain a first training image; wherein the first training image includes a position annotation, a region name annotation, and an icing difficulty value of each region; Normalizing the first training image to obtain a second training image; The second training image is input into the initial target recognition model for training to obtain a trained target recognition model; the initial target recognition model is constructed based on the FasterR-CNN algorithm or the YOLO algorithm.

[0008] As some optional implementations of the present application, the step of determining whether to start the aircraft automatic de-icing system for de-icing processing based on the icing signal information includes: Comparing the icing difficulty level value of the target area with a preset icing difficulty level threshold, and if the icing difficulty level value of the target area is greater than or equal to the preset icing difficulty level threshold, starting the aircraft automatic de-icing system to perform de-icing processing; If the icing difficulty level value of the target area is less than the preset icing difficulty level threshold, the number of target areas is compared with the preset number, and if the number of target areas is greater than or equal to the preset number, the aircraft automatic de-icing system is turned on to perform de-icing processing; If the number of the target areas is less than the preset number, the ice layer thickness of each target area is compared with a preset thickness threshold, and de-icing is performed on the target areas with ice layer thickness greater than or equal to the preset thickness threshold.

[0009] As some optional implementations of the present application, the step of comparing the ice layer thickness of each target area with a preset thickness threshold and performing deicing treatment on the target area where the ice layer thickness is greater than or equal to the preset thickness threshold includes: Comparing the ice thickness of each of the target areas with a first thickness threshold; If the ice thickness is greater than or equal to the first thickness threshold, the ice thickness is compared with the second thickness threshold, and if the ice thickness is greater than or equal to the first thickness threshold but less than the second thickness threshold, a first ice alarm signal is sent to the user terminal; the first ice alarm signal includes a signal requiring manual confirmation; If the ice thickness is greater than or equal to the second thickness threshold, the ice thickness is compared with a third thickness threshold; if the ice thickness is greater than or equal to the second thickness threshold but less than the third thickness threshold, a deicing device corresponding to the target area is turned on; If the ice thickness is greater than or equal to the third thickness threshold, the aircraft automatic de-icing system is turned on to perform de-icing processing; Among them, the first thickness threshold < the second thickness threshold < the third thickness threshold.

[0010] As some optional implementation modes of the present application, after the step of sending the first icing warning signal to the user terminal, the method further includes: Receiving a manual confirmation signal fed back by the user terminal; If the manual confirmation signal is an on signal, the automatic de-icing system of the aircraft is turned on to perform de-icing processing, and the electric heating de-icing system of the ultrasonic pulse echo icing sensor is turned on at the same time, so that the ultrasonic pulse echo icing sensor signal can work normally after being reset; If the manual confirmation signal is not to be processed temporarily, the detection is continued based on the ice thickness of each target area.

[0011] In order to solve the above technical problems, the present application also provides: an intelligent deicing system, the system comprising: A temperature detection device, used to detect the aircraft surface temperature based on the infrared sensor to obtain the aircraft surface temperature value; compare the aircraft surface temperature value with a temperature threshold; if the aircraft surface temperature value is greater than the temperature threshold, continue to detect the aircraft surface temperature based on the infrared sensor; an ultrasonic pulse echo icing sensor, for turning on the ultrasonic pulse echo icing sensor to detect the ice thickness on the aircraft surface and obtain icing signal information if the aircraft surface temperature value is less than or equal to the temperature threshold; The data processing device is used to determine whether to start the aircraft automatic de-icing system to perform de-icing processing based on the icing signal information.

[0012] As some optional embodiments of the present application, the ultrasonic pulse echo icing sensor includes: a delay block, a piezoelectric ceramic layer, a matching layer, a backing, an electric thermal deicing system, a housing, a signal transmitting and receiving circuit, a signal processing circuit and a host computer; The delay block is used to separate the aluminum-ice interface signal and the ice-air interface signal; The thickness of the delay block satisfies the following relationship: , where is the longitudinal wave speed of the delay block, is the longitudinal wave speed of the ice layer, is the thickness of the delay line, It is the target value for measuring ice thickness.

[0013] In order to solve the above technical problems, the present application also provides: a computer-readable storage medium, on which a computer program is stored, and a processor executes the computer program to implement the above method.

[0014] To solve the above technical problems, the present application also provides: an electronic device, comprising a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the above method.

[0015] Compared with the prior art, the intelligent deicing method described in the embodiment of the present application has the following advantages: 1) Accurate surface temperature detection and ice thickness measurement: In traditional methods, de-icing systems are usually triggered at fixed time intervals or based on manual inspections by pilots. In contrast, the method described in this application uses infrared sensors to detect the aircraft surface temperature in real time and dynamically adjusts operations based on actual conditions, thereby providing more accurate and real-time surface temperature data. Ultrasonic pulse echo ice sensor detection is further performed based on the detection results of the infrared sensor to accurately measure the ice thickness on the aircraft surface, greatly improving the accuracy and reliability of the measurement compared to traditional visual or manual inspections.

[0016] 2) Automated de-icing decision process: Traditional methods usually rely on the judgment and decision of the pilot, while the method described in this application realizes an automated decision process by combining infrared and ultrasonic pulse echo technology. Based on the acquired icing signal information, the system can independently judge and execute whether to start the aircraft's automatic de-icing system, thereby reducing the errors and delays caused by human judgment.

[0017] 3) Enhanced safety and operational efficiency: Since the temperature and icing conditions of the aircraft surface can be detected and automatically responded to in real time, the method described in this application greatly improves the safety of aircraft operation. The timely activation and precise deicing of the aircraft automatic deicing system can reduce the impact of icing on the aircraft's aerodynamic performance and flight safety, while reducing the frequency of manual operation, improving operational efficiency, and achieving low-power precision deicing.

[0018] 4) Target recognition model based on machine learning: This method also introduces a target recognition model, which can identify the icing conditions of different parts of the aircraft surface through machine learning training, further enhancing the system's ability to perceive the icing state of the aircraft. Compared with traditional manual inspection, this target recognition technology significantly improves the intelligence level of the system.

[0019] It can be seen that the intelligent de-icing method described in the present application has significant improvements in accuracy, degree of automation, safety and operational efficiency compared with traditional technologies, greatly improving the efficiency of aircraft de-icing. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the specific implementation of the present application or the technical solution in the prior art, the following is a brief introduction to the drawings required for the specific implementation or the prior art description. In all drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, each element or part is not necessarily drawn according to the actual scale.

[0021] Figure 1 A schematic diagram of the computer device structure of the hardware operating environment involved in this application; Figure 2 A schematic diagram of the process of the intelligent deicing method based on ultrasonic detection involved in this application; Figure 3 A schematic diagram of the structure of an intelligent deicing system involved in this application; Figure 4 A front view of the ultrasonic pulse echo icing sensor involved in the present application; Figure 5 is a cross-sectional view of the ultrasonic pulse echo icing sensor involved in the present application; Figure 6 The cross-sectional structure of the piezoelectric transducer involved in this application; Figure 7 It is a schematic diagram of signal transmission of the ultrasonic pulse echo icing sensor involved in the present application in a working state; Figure 8 It is a schematic diagram of the signal detection result of the ultrasonic pulse echo icing sensor involved in the present application in a working state; In the figure, 1 represents an ice-sensitive surface, 2 represents a threaded hole, 3 represents a mounting hole, 4 represents a wire outlet slot, 5 represents a delay block, 6 represents a heating plate, 7 represents a piezoelectric transducer, 8 represents a connecting plate, 9 represents a mounting flange, 10 represents a matching layer, 11 represents a piezoelectric ceramic layer, and 12 represents a backing.

[0022] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0024] It should be noted that all directional indications in the embodiments of the present application (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0025] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0026] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present application, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing in the full text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in the field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0027] Reference Figure 1 , Figure 1 This is a schematic diagram of the computer device structure of the hardware operating environment involved in this embodiment, such as Figure 1As shown, the computer device may include: a processor 1001, such as a central processing unit (CPU), a communication bus 1002, a user interface 1003, a network interface 1004, and a memory 1005. Among them, the communication bus 1002 is used to realize the connection and communication between these components. The user interface 1003 may include a display screen (Display), an input unit such as a keyboard (Keyboard), and the optional user interface 1003 may also include a standard wired interface and a wireless interface. The network interface 1004 may optionally include a standard wired interface and a wireless interface (such as a wireless fidelity (WIreless-FIdelity, WI-FI) interface). The memory 1005 may be a high-speed random access memory (Random Access Memory, RAM) memory, or a stable non-volatile memory (Non-Volatile Memory, NVM), such as a disk memory. The memory 1005 may also be a storage device independent of the aforementioned processor 1001.

[0028] Those skilled in the art will understand that Figure 1 The structure shown in the figure does not constitute a limitation on the computer device, and may include more or less components than shown in the figure, or combine some components, or arrange the components differently.

[0029] like Figure 1 As shown, the memory 1005 as a storage medium may include an operating system, a network communication module, a user interface module, and an electronic program, and may also include a data storage module.

[0030] exist Figure 1 In the computer device shown, the network interface 1004 is mainly used for data communication with the network server; the user interface 1003 is mainly used for data interaction with the user; the processor 1001 and the memory 1005 in the computer device of this embodiment can be set in the computer device, and the computer device calls the intelligent deicing system stored in the memory 1005 through the processor 1001, and executes the intelligent deicing method provided in this embodiment.

[0031] It should be noted that the above-mentioned computer device may be an external hardware device that can operate independently, or may be a hardware device that is built into the intelligent deicing system.

[0032] Reference Figure 2 Based on the aforementioned hardware environment, this embodiment further provides an intelligent deicing method based on ultrasonic detection, which is used in an intelligent deicing system. The method includes the following steps: Step S10: detecting the aircraft surface temperature based on the infrared sensor to obtain an aircraft surface temperature value; and comparing the aircraft surface temperature value with a temperature threshold.

[0033] It should be noted that the infrared sensor can be a non-contact infrared temperature sensor. When detecting the surface temperature of the aircraft, it can be a periodic or continuous temperature detection, and can be set based on actual flight conditions to ensure the accuracy and precision of the sensor so as to effectively obtain the temperature value of the aircraft surface.

[0034] The temperature threshold may be specified by the aircraft manufacturer or operating manual to ensure that the aircraft surface temperature does not cause icing or other safety issues. By comparing the aircraft surface temperature value with the temperature threshold, the following situations may occur: When the aircraft surface temperature is higher than the temperature threshold: Continue to use the infrared sensor to detect the temperature to avoid icing caused by lower temperature.

[0035] When the aircraft surface temperature is lower than or equal to the temperature threshold: the ultrasonic pulse echo icing sensor is activated. The ultrasonic pulse echo icing sensor is capable of sending ultrasonic pulses and receiving their reflected echoes to detect the thickness of the ice layer on the aircraft surface. The reflected echo signal received by the ultrasonic pulse echo sensor is then analyzed to determine whether there is ice on the aircraft surface and the thickness of the ice. This may involve signal processing algorithms, such as time domain reflectometry (TDR) or other digital signal processing methods to determine the extent and location of ice.

[0036] The system will make a decision to determine whether to turn on the aircraft's automatic de-icing system, that is, based on the icing signal information. If the icing exceeds the safety limit or other preset conditions, the aircraft's de-icing system will be automatically activated. The automatic de-icing system may include a spraying system that uses hot air or chemical de-icing liquid to melt and remove icing material from the aircraft surface.

[0037] Through the above steps, it can be ensured that the aircraft can operate safely in all weather conditions, respond to possible icing problems in a timely manner, and improve flight safety and efficiency.

[0038] For example, the surface temperature of an aircraft varies during flight due to changes in air flow and altitude conditions. Airlines or aircraft manufacturers may set the following temperature threshold strategy: 1. Temperature threshold setting: Above 0℃: When the aircraft surface temperature is above 0℃, the risk of icing may be low. The de-icing system will not be activated at this time.

[0039] 0℃ to -10℃: In this temperature range, water droplets on the aircraft surface may cool rapidly and freeze, with a medium to high risk. The aircraft system will continuously monitor and consider activating the de-icing system.

[0040] Below -10°C: At extremely low temperatures, the risk of icing increases significantly. The aircraft may immediately activate its automatic de-icing system to keep surfaces free of ice.

[0041] Furthermore, when the aircraft surface temperature reaches below 0°C, the automatic control system will activate the ice detection device (such as an ultrasonic pulse echo sensor) to detect the thickness of the ice layer. If it is detected that the ice layer exceeds the preset safety thickness, the aircraft will automatically activate the de-icing system, such as spraying de-icing liquid or using hot air flow to remove ice.

[0042] Of course, in actual application scenarios, airlines or aircraft operation teams usually adjust temperature thresholds based on meteorological data, aircraft models, and operating history. For example, climate conditions in certain regions may lead to higher icing risks, requiring more conservative threshold settings. Temperature data can also be continuously updated and icing risk assessments can be performed through a real-time monitoring system to ensure that the aircraft can operate safely throughout the flight.

[0043] In the above cases, we can see that the aircraft makes intelligent decisions based on the surface temperature and the preset temperature threshold during flight to ensure flight safety and efficiency. This strategy not only relies on the rationality of the temperature threshold setting, but also needs to take into account the comprehensive factors of real-time environmental conditions and flight safety.

[0044] Specifically, as described in the following steps S20 to S30: Step S20: If the aircraft surface temperature value is greater than the temperature threshold, continue to detect the aircraft surface temperature based on the infrared sensor.

[0045] This step can detect the temperature of the aircraft surface in real time and respond immediately when the temperature exceeds the preset threshold. This real-time response capability allows the aircraft to quickly adapt to different environmental conditions, thereby effectively reducing the risk of icing. For example, infrared sensors can quickly and accurately obtain temperature data on the aircraft surface, usually in a non-contact manner, so there will be no damage or interference to the aircraft surface. This high-frequency temperature detection can capture subtle differences in temperature changes, ensuring that necessary measures are taken in a timely manner when the aircraft surface temperature exceeds the threshold.

[0046] Step S30: If the aircraft surface temperature value is less than or equal to the temperature threshold, the ultrasonic pulse echo icing sensor is turned on to detect the ice thickness on the aircraft surface to obtain icing signal information.

[0047] That is, when the aircraft surface temperature value is less than or equal to the preset temperature threshold, the system will start the ultrasonic pulse echo icing sensor. This sensor measures the thickness of ice on the aircraft surface by sending ultrasonic pulses and receiving reflected waves. The sensor analyzes the returned signal to determine the thickness and distribution of the ice layer. This enables flight operators to accurately understand the icing conditions on the aircraft surface and make corresponding de-icing decisions based on real-time data to ensure that the aircraft maintains a minimized or ice-free state during flight, thereby improving flight safety. It also allows operators to quickly respond to icing conditions on the aircraft surface and initiate necessary de-icing measures. By obtaining icing signal information in real time, the negative impact of icing on flight performance and safety can be effectively avoided, ensuring the smooth progress of flight.

[0048] In a further embodiment, if the aircraft surface temperature value is less than or equal to the temperature threshold in step S30, the ultrasonic pulse echo icing sensor is turned on to detect the ice thickness on the aircraft surface, and the step of obtaining icing signal information includes: Step S31: If the aircraft surface temperature value is less than or equal to the temperature threshold, the target area is photographed based on the image acquisition device to obtain multiple images of the target area.

[0049] That is, a preset image acquisition device is used to photograph multiple target areas on the aircraft surface. These target areas are usually parts that are easily affected by icing, such as wings, air inlets, etc.; further, the multi-angle, high-definition images obtained help to improve the accuracy of subsequent target recognition and icing detection.

[0050] Step S32: input the images of each target area into the trained target recognition model to obtain the target area information corresponding to the images of each target area; the target area information includes the target area position and the target area icing difficulty level value.

[0051] That is, the collected image set is input into a pre-trained target recognition model so that the model analyzes the image of each target area and identifies the target area information contained in the image; the target area information includes the location of the target area and the ice difficulty value.

[0052] It should be noted that the target recognition model is trained through the following steps: Acquire an aircraft image set; the aircraft image set includes aircraft images of different models of aircraft at different angles and in different states; Performing feature annotation on each region in the aircraft image to obtain a first training image; wherein the first training image includes a position annotation, a region name annotation, and an icing difficulty value of each region; Normalizing the first training image to obtain a second training image; The second training image is input into the initial target recognition model for training to obtain a trained target recognition model; the initial target recognition model is constructed based on the FasterR-CNN algorithm or the YOLO algorithm.

[0053] Step S33: based on the target area information, start the ultrasonic pulse echo icing sensor, perform icing thickness detection on the target area, and obtain the icing layer thickness of the target area.

[0054] That is, according to the target area information output by the target recognition model, the area where the ice thickness detection is required is determined. Then, the ultrasonic pulse echo ice sensor is used to detect the ice thickness in each target area in real time. The result feedback of the ice layer thickness is provided to the pilot or the automation system for further decision-making, such as whether de-icing operation is required.

[0055] It can be seen that the above steps use modern technology to achieve automated detection, reduce errors and delays in human operations, and improve the real-time and accuracy of detection; and combine the data of temperature sensors, image acquisition devices, and ultrasonic pulse echo sensors to provide a more comprehensive evaluation of icing conditions through comprehensive analysis; and through target recognition and ice thickness detection, provide pilots or autopilot systems with instant icing condition reports to help make reasonable flight operation decisions and ensure flight safety. That is, the above scheme combines advanced sensing technology and deep learning models to provide a complete solution for aircraft icing detection, which can effectively deal with icing problems in different flight environments and improve flight safety and operational efficiency.

[0056] Step S40: Based on the icing signal information, determine whether to start the aircraft automatic de-icing system to perform de-icing processing.

[0057] The step of determining whether to start the aircraft automatic de-icing system to perform de-icing processing based on the icing signal information in step S40 includes: Step S41, comparing the icing difficulty level value of the target area with a preset icing difficulty level threshold, if the icing difficulty level value of the target area is greater than or equal to the preset icing difficulty level threshold, starting the aircraft automatic de-icing system to perform de-icing processing; Step S42: if the icing difficulty level value of the target area is less than the preset icing difficulty level threshold, the number of target areas is compared with the preset number; if the number of target areas is greater than or equal to the preset number, the automatic de-icing system of the aircraft is started to perform de-icing processing; Step S43: If the number of the target areas is less than the preset number, the ice layer thickness of each target area is compared with a preset thickness threshold, and de-icing is performed on the target areas with ice layer thickness greater than or equal to the preset thickness threshold.

[0058] It can be seen that the above steps can accurately determine whether de-icing is needed by real-time detection and evaluation of the difficulty of icing in the target area, thereby avoiding unnecessary operations and energy consumption. The automated judgment and processing mechanism enables the system to respond quickly to icing conditions without manual intervention, improving operational efficiency and safety.

[0059] In addition, considering that there may be multiple icing areas on the aircraft surface, the urgency of de-icing can be judged by comparing the number of areas, thereby improving the safety and reliability of the aircraft surface. In addition, by distinguishing the thickness of the ice layer in different areas, the system can carry out de-icing in a targeted manner, avoiding wasteful operations on areas that may not need to be processed, and improving energy efficiency and operation accuracy. Ensuring that de-icing operations are performed only when they are really needed effectively reduces the risk of icing on the aircraft surface and improves navigation safety.

[0060] Through the above steps, the aircraft automatic de-icing system can intelligently determine whether to perform de-icing according to the actual situation and preset conditions, thereby ensuring flight safety and operational efficiency to the greatest extent. Through accurate icing level assessment, area quantity inspection and thickness comparison, the system can not only comprehensively cover the icing problems on the aircraft surface, but also optimize resource utilization and improve the real-time and accuracy of de-icing operations.

[0061] For example, suppose an aircraft is flying and encounters snowfall. The automatic de-icing system on the aircraft surface determines whether de-icing is required through the following steps: Step S41: Ice and snow begin to accumulate on the wing surface of the aircraft. The image acquisition device captures the icing on the wing in real time and compares its icing level with the preset icing level threshold. The image processing software analyzes the icing on the wing and determines that the icing level is 3 (for example, the ice thickness exceeds 2 mm). The preset icing level threshold is 2 (the ice thickness is less than 2 mm). Since the icing level of the wing is 3, which is higher than the preset threshold 2, the system determines that the aircraft automatic de-icing system needs to be immediately turned on for de-icing.

[0062] Step S42: The fuselage and vertical tail of the aircraft also begin to show local icing. The system further detects the number of areas that need de-icing. The system identifies that there are 2 areas of the fuselage and 1 area of ​​the vertical tail that are iced, for a total of 3 target areas. The preset number threshold is 2 areas. Because the actual number of target areas found (3) exceeds the preset number threshold, the system decides to continue to turn on the automatic de-icing system and uniformly handle all iced areas to avoid the pilot having to manually turn on the de-icing devices in multiple areas in turn, which will cause the icing phenomenon to become more serious and affect the safe flight of the aircraft.

[0063] Step S43: When the number of target areas is less than the preset number threshold, such as the number of target areas is 1, the system further analyzes the thickness of the ice layer in each target area. For example, the system measures that the thickness of the ice area on the vertical tail is 6 mm. The preset thickness threshold is 2 mm. Since the thickness of the ice layer on the vertical tail exceeds the preset thickness threshold, it means that the icing phenomenon is about to worsen, so the system will also perform unified deicing treatment on all areas.

[0064] It can be seen that through the above steps S41-S43, the icing condition of the aircraft surface can be detected and evaluated in real time, so as to accurately determine which parts need to be de-iced, avoiding unnecessary operations and energy waste; and through continuous judgment of multiple steps, the system ensures the integrity and accuracy of the entire aircraft surface coverage, improving flight safety; and the automated operation of the system not only improves operational efficiency, but also reduces the impact of human factors on de-icing decisions, ensuring safe flight under complex weather conditions.

[0065] In another example, the step of comparing the ice layer thickness of each target area with a preset thickness threshold and performing de-icing treatment on the target area with an ice layer thickness greater than or equal to the preset thickness threshold comprises: Comparing the ice thickness of each of the target areas with a first thickness threshold; If the ice thickness is greater than or equal to the first thickness threshold, the ice thickness is compared with the second thickness threshold, and if the ice thickness is greater than or equal to the first thickness threshold but less than the second thickness threshold, a first ice alarm signal is sent to the user terminal; the first ice alarm signal includes a signal requiring manual confirmation; If the ice thickness is greater than or equal to the second thickness threshold, the ice thickness is compared with a third thickness threshold; if the ice thickness is greater than or equal to the second thickness threshold but less than the third thickness threshold, a deicing device corresponding to the target area is turned on; If the ice thickness is greater than or equal to the third thickness threshold, the aircraft automatic de-icing system is turned on to perform de-icing processing; Among them, the first thickness threshold < the second thickness threshold < the third thickness threshold.

[0066] It can be seen that the above steps introduce multi-level ice thickness judgment and corresponding processing steps based on the original plan. The refined plan adopts different treatment measures according to the thickness of the ice layer, rather than simply carrying out de-icing treatment in a one-size-fits-all manner. This strategy can take more appropriate and accurate treatment methods according to the specific severity of the icing situation, effectively improving the efficiency and effect of de-icing. In addition, the introduction of icing alarm signals and signals requiring manual confirmation, as well as the process of starting the de-icing device and the automatic de-icing system, these mechanisms help to promptly alert relevant operators, thereby avoiding the de-icing situation from worsening.

[0067] At the same time, a step-by-step processing flow is provided, that is, the solution clearly defines the processing steps under different thresholds, such as the first thickness threshold triggers an alarm, the second thickness threshold activates the deicing device, and the third thickness threshold activates the automatic deicing system. This step-by-step processing flow helps to improve the intelligence and automation of the system, reduce the need for manual intervention, and improve the response speed and efficiency of the system.

[0068] The thickness threshold can be adjusted and customized according to specific scenarios and requirements, so that the system can adapt to icing conditions in different environments and can flexibly respond to different deicing requirements, thereby improving the versatility and adaptability of the system. For example, it can be set as follows: the first thickness threshold is 0.06 mm, the second thickness threshold is 1 mm, and the third thickness threshold is 2 mm.

[0069] In addition, a user-side feedback and interaction process is set up, that is, sending icing alarm signals and signals requiring manual confirmation to the user side, so that users can understand the icing situation in a timely manner and take corresponding measures. This feedback mechanism helps to improve the operability of the overall system and user experience.

[0070] In a further scheme, after the step of sending the first icing warning signal to the user end, it also includes: receiving a manual confirmation signal fed back by the user end; if the manual confirmation signal is an on signal, starting the aircraft automatic de-icing system to perform de-icing processing, and at the same time starting the electric thermal de-icing system of the ultrasonic pulse echo icing sensor, so that the ultrasonic pulse echo icing sensor signal can work normally after being reset; if the manual confirmation signal is not to be processed temporarily, continuing to detect based on the ice thickness of each of the target areas.

[0071] That is, it allows flexible selection of processing methods based on received user feedback signals. By distinguishing between turn-on signals and non-processing signals, the controllability of the system is enhanced, enabling appropriate decisions and responses to be made based on actual conditions. This flexibility can better cope with different icing conditions and flight conditions. In addition, the coordinated operation of the aircraft's automatic de-icing system and the ultrasonic pulse echo icing sensor's electrothermal de-icing system is limited. This integration ensures that when the turn-on signal is received, both systems are turned on at the same time, thereby performing de-icing more quickly. This not only improves operational efficiency, but also reduces the need for manual intervention and the possibility of misoperation.

[0072] It should be noted that the normal operation of the ultrasonic pulse echo icing sensor signal after being reset means that the ultrasonic pulse echo icing sensor signal is infinitely close to 0 and the signal remains stable.

[0073] On the other hand, Figure 3 As shown, in order to solve the above technical problems, the embodiment of the present application further provides: an intelligent deicing system, the system comprising: A temperature detection device, used to detect the aircraft surface temperature based on the infrared sensor to obtain the aircraft surface temperature value; compare the aircraft surface temperature value with a temperature threshold; if the aircraft surface temperature value is greater than the temperature threshold, continue to detect the aircraft surface temperature based on the infrared sensor; an ultrasonic pulse echo icing sensor, for turning on the ultrasonic pulse echo icing sensor to detect the ice thickness on the aircraft surface and obtain icing signal information if the aircraft surface temperature value is less than or equal to the temperature threshold; The data processing device is used to determine whether to start the aircraft automatic de-icing system to perform de-icing processing based on the icing signal information.

[0074] The ultrasonic pulse echo icing sensor includes: a delay block, a piezoelectric ceramic layer, a matching layer, a backing, an electric heating deicing system, a housing, a signal transmitting and receiving circuit, a signal processing circuit and a host computer; The delay block is used to separate the aluminum-ice interface signal and the ice-air interface signal; The thickness of the delay block satisfies the following relationship: , where is the longitudinal wave speed of the delay block, is the longitudinal wave speed of the ice layer, is the thickness of the delay line, It is the target value for measuring ice thickness.

[0075] For example, the longitudinal wave sound speed in aluminum is 6300m / s, the longitudinal wave sound speed in ice is 3230m / s, and the upper limit of ice layer thickness detection is designed to be 10mm, so the thickness of the aluminum delay structure needs to be greater than 19.5mm.

[0076] The piezoelectric ceramic layer is used to convert the electrical signal into a vibration signal to stimulate an ultrasonic pulse wave. The matching layer matches the acoustic impedance of the piezoelectric ceramic and the aluminum layer to reduce signal distortion and improve the signal-to-noise ratio. The backing is used to attenuate the ultrasonic pulse wave to prevent interference with the received signal. The electrothermal deicing system is used to remove the ice layer on the probe. The signal transmitting and receiving circuit is used to generate a high-voltage pulse signal and receive a pulse echo signal. The signal processing circuit is used to amplify, pre-filter, and AD convert the signal; run relevant algorithms, perform algorithm analysis on the signal, and output an ice thickness signal. The host computer is used to adjust relevant algorithm parameters, post-process the signal, debug the sensor, and burn the program code.

[0077] The front view of the ultrasonic pulse echo icing sensor is as follows Figure 4 As shown, Figure 4 In the figure: 1 indicates the ice sensitive surface, 2 indicates the threaded hole, 3 indicates the mounting hole, and 4 indicates the outlet groove. The ultrasonic pulse echo ice sensor is usually installed on the belly of the aircraft. The specific installation position needs to be calculated and tested according to the different types of aircraft to obtain the best installation position, which is not specifically limited here.

[0078] The cross-sectional view of the ultrasonic pulse echo icing sensor is as follows: Figure 5 As shown, Figure 5 In the middle: 5 represents a delay block, 6 represents a heating plate, 7 represents a piezoelectric transducer, 8 represents a connecting plate, and 9 represents a mounting flange.

[0079] The cross-sectional view of the piezoelectric transducer is as follows Figure 6 As shown, Figure 6 In the middle: 10 denotes a matching layer, 11 denotes a piezoelectric ceramic layer, and 12 denotes a backing.

[0080] In actual work, Figure 7 As shown in the figure, the piezoelectric ceramic layer converts the pulse voltage signal into a mechanical vibration signal, generating an ultrasonic pulse wave, which passes through the matching layer and enters the delay block. Figure 8 As shown, the pulse echo signal is reflected at the interface between the delay block and the ice layer, and the other part is transmitted into the ice layer and reflected at the top of the ice layer (interface between the ice layer and the air) to form a pulse echo signal. These two pulse echo signals are separated by the delay structure and propagated to the piezoelectric ceramic receiver, which converts the vibration signal into a voltage signal to identify the thickness of the ice layer. The backing material is mainly used to attenuate the pulse echo and reduce the interference with the receiving signal of the piezoelectric ceramic layer.

[0081] It can be seen that the above system has several significant advantages: Accurate ice detection and de-icing trigger mechanism: The system uses infrared sensors to accurately detect the temperature of the aircraft surface. Once the temperature is below the preset threshold, the ultrasonic pulse echo ice sensor can be activated. This dual detection mechanism based on temperature and ice thickness effectively ensures that the de-icing system is activated at the necessary time to prevent ice from causing danger to the aircraft.

[0082] Efficient ice thickness measurement and data processing capabilities: The ultrasonic pulse echo ice sensor uses its complex sensor structure and signal processing circuit to accurately measure the ice thickness on the aircraft surface. Through amplification, filtering, AD conversion and other processing, it ensures that the acquired ice signal information is accurate and reliable, thereby triggering the correct de-icing process.

[0083] Strong adaptability and high adjustability: The system's host computer allows adjustment of algorithm parameters and post-processing to adapt to the de-icing needs of different aircraft models and different environmental conditions. This flexibility enables the system to perform well in various flight conditions and ensure flight safety.

[0084] Advanced technology and high reliability: Utilizing modern ultrasonic pulse technology and electric heating deicing system, the system not only has efficient ice detection capabilities, but also can quickly and reliably perform deicing. The structural design and functional configuration of each component enable the system to operate stably in severe weather and complex operating environments.

[0085] Combination of safety and economy: Through accurate ice detection and precise de-icing, the system not only ensures flight safety, but also effectively reduces de-icing frequency and resource consumption, thus achieving a good balance between safety and economy.

[0086] That is, through technological innovation and precise engineering design, the aircraft's operational safety and efficiency in severe weather conditions are improved.

[0087] Based on the same inventive concept as the aforementioned embodiment, this embodiment provides a computer-readable storage medium, on which a computer program is stored, and a processor executes the computer program to implement the aforementioned method.

[0088] In some embodiments, the computer readable storage medium may be a memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash memory, magnetic surface memory, optical disk, or CD-ROM; or various devices including one or any combination of the above memories. The computer may be various computing devices including intelligent terminals and servers.

[0089] The above are only preferred embodiments of the present application, and are not intended to limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. An intelligent deicing method based on ultrasonic detection, characterized in that: For use in an intelligent deicing system, the method comprises the following steps: Detecting the aircraft surface temperature based on an infrared sensor to obtain an aircraft surface temperature value; comparing the aircraft surface temperature value with a temperature threshold; If the aircraft surface temperature value is greater than the temperature threshold, continue to detect the aircraft surface temperature based on the infrared sensor; If the aircraft surface temperature value is less than or equal to the temperature threshold, the ultrasonic pulse echo icing sensor is turned on to detect the ice thickness on the aircraft surface to obtain icing signal information; Based on the icing signal information, it is determined whether to start the automatic de-icing system of the aircraft to perform de-icing processing.

2. The intelligent deicing method based on ultrasonic detection according to claim 1 is characterized in that: If the aircraft surface temperature value is less than or equal to the temperature threshold, the ultrasonic pulse echo icing sensor is turned on to detect the icing thickness on the aircraft surface to obtain icing signal information, including: If the aircraft surface temperature value is less than or equal to the temperature threshold, the target area is photographed based on the image acquisition device to obtain multiple images of the target area; the target area refers to an area where the surface temperature value is less than or equal to the temperature threshold; Inputting the images of each target area into the trained target recognition model to obtain target area information corresponding to the images of each target area; the target area information includes the target area location and the icing difficulty level value of the target area; Based on the target area information, the ultrasonic pulse echo icing sensor is turned on to detect the ice thickness of the target area to obtain the ice layer thickness of the target area.

3. The intelligent deicing method based on ultrasonic detection according to claim 2 is characterized in that: The target recognition model is trained by the following steps: Acquire an aircraft image set; the aircraft image set includes aircraft images of different models of aircraft at different angles and in different states; Performing feature annotation on each region in the aircraft image to obtain a first training image; wherein the first training image includes a position annotation, a region name annotation, and an icing difficulty value of each region; Normalizing the first training image to obtain a second training image; The second training image is input into the initial target recognition model for training to obtain a trained target recognition model; the initial target recognition model is constructed based on the FasterR-CNN algorithm or the YOLO algorithm.

4. The intelligent deicing method based on ultrasonic detection according to claim 2 is characterized in that: The step of determining whether to start the aircraft automatic de-icing system to perform de-icing processing based on the icing signal information includes: Comparing the icing difficulty level value of the target area with a preset icing difficulty level threshold, and if the icing difficulty level value of the target area is greater than or equal to the preset icing difficulty level threshold, starting the aircraft automatic de-icing system to perform de-icing processing; If the icing difficulty level value of the target area is less than the preset icing difficulty level threshold, the number of target areas is compared with the preset number, and if the number of target areas is greater than or equal to the preset number, the aircraft automatic de-icing system is turned on to perform de-icing processing; If the number of the target areas is less than the preset number, the ice layer thickness of each target area is compared with a preset thickness threshold, and de-icing is performed on the target areas with ice layer thickness greater than or equal to the preset thickness threshold.

5. The intelligent deicing method based on ultrasonic detection according to claim 4 is characterized in that: The step of comparing the ice layer thickness of each target area with a preset thickness threshold and performing de-icing on the target area with an ice layer thickness greater than or equal to the preset thickness threshold comprises: Comparing the ice thickness of each of the target areas with a first thickness threshold; If the ice thickness is greater than or equal to the first thickness threshold, the ice thickness is compared with the second thickness threshold, and if the ice thickness is greater than or equal to the first thickness threshold but less than the second thickness threshold, a first ice alarm signal is sent to the user terminal; the first ice alarm signal includes a signal requiring manual confirmation; If the ice thickness is greater than or equal to the second thickness threshold, the ice thickness is compared with a third thickness threshold; if the ice thickness is greater than or equal to the second thickness threshold but less than the third thickness threshold, a deicing device corresponding to the target area is turned on; If the ice thickness is greater than or equal to the third thickness threshold, the aircraft automatic de-icing system is turned on to perform de-icing processing; Among them, the first thickness threshold < the second thickness threshold < the third thickness threshold.

6. The intelligent deicing method based on ultrasonic detection according to claim 5 is characterized in that: After the step of sending the first icing alarm signal to the user terminal, the method further includes: Receiving a manual confirmation signal fed back by the user terminal; If the manual confirmation signal is an on signal, the automatic de-icing system of the aircraft is turned on to perform de-icing processing, and the electric heating de-icing system of the ultrasonic pulse echo icing sensor is turned on at the same time, so that the ultrasonic pulse echo icing sensor signal can work normally after being reset; If the manual confirmation signal is not to be processed temporarily, the detection is continued based on the ice thickness of each target area.

7. An intelligent deicing system, characterized in that: The system includes: A temperature detection device, used to detect the aircraft surface temperature based on the infrared sensor to obtain the aircraft surface temperature value; compare the aircraft surface temperature value with a temperature threshold; if the aircraft surface temperature value is greater than the temperature threshold, continue to detect the aircraft surface temperature based on the infrared sensor; an ultrasonic pulse echo icing sensor, for turning on the ultrasonic pulse echo icing sensor to detect the ice thickness on the aircraft surface and obtain icing signal information if the aircraft surface temperature value is less than or equal to the temperature threshold; The data processing device is used to determine whether to start the aircraft automatic de-icing system to perform de-icing processing based on the icing signal information.

8. The intelligent deicing system according to claim 7, characterized in that: The ultrasonic pulse echo icing sensor comprises: a delay block, a piezoelectric ceramic layer, a matching layer, a backing, an electric heating deicing system, a housing, a signal transmitting and receiving circuit, a signal processing circuit and a host computer; The delay block is used to separate the aluminum-ice interface signal and the ice-air interface signal; The thickness of the delay block satisfies the following relationship: , where is the longitudinal wave speed of the delay block, is the longitudinal wave speed of the ice layer, is the thickness of the delay line, It is the target value for measuring ice thickness.

9. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and the processor executes the computer program to implement the method according to any one of claims 1 to 6.

10. An electronic device, characterized in that: The electronic device comprises a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the method according to any one of claims 1 to 6.

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